Compression spring latch pop-off separation mechanism for split-body flying wing layout aircraft

Abstract

The application discloses a compression spring lock buckle pop-up type separation mechanism for a separable flying wing layout aircraft, which comprises a main machine connecting rod, a submachine nesting rod and a submachine separation mechanism, the submachine separation mechanism comprises a limiting block, a guide rail, a central fixed block, a guide rail sliding block, a guide rod, a spring arranged on the guide rod and abutting against the limiting block at one end and the central fixed block at the other end, and a constraint assembly for locking the position of the limiting block and compressing the spring, the constraint assembly releases the limiting constraint on the limiting block, the limiting block moves to the outside of the guide rail together with the guide rail sliding block under the rebound force of the spring, the limiting block is separated from the tail end of the main machine connecting rod, the sub-aircraft moves backward, the submachine nesting rod is separated from the nesting actuating 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 application improves the stability of combined flight and the structural reliability by limiting the relative pitching between the long machine and the submachine.

Description

TECHNICAL FIELD

[0001] The present application relates to a separation mechanism of a main aircraft and a sub-aircraft, and in particular to a compression spring lock buckle pop-up separation mechanism for a split-body flying wing layout aircraft. BACKGROUND

[0002] The split-body layout is a new type of aircraft layout scheme, which can fully exert the advantages of the split-body aircraft combination and its individual, and integrate the multi-unmanned aerial vehicle cluster flight control technology, further improve the multi-task execution capability of the aircraft, and greatly expand the use of the aircraft.

[0003] The split-body combination of the aircraft involves the design of the separation combination device and control, and needs strong flight control programs to support. During the separation of the mother aircraft and the sub-aircraft, due to the complex unsteady airflow interference, physical collision between the aircrafts may occur, thereby affecting the separation safety. The prior application (2022106735928) discloses a split-body flying wing layout unmanned aircraft, in which in order to ensure that the combination aircraft can be stably connected, the number of previous sub-aircraft separation mechanisms arranged is too large, the number of parts is large, and the quality is too heavy due to the fact that the previous sub-aircraft separation mechanisms are not compact enough, thereby reducing the effective payload of the aircraft. In addition, there is a high static instability, if the manufacturing precision cannot reach the specified tolerance, it will cause installation difficulty; the guide rail slider adopts a non-standard part, and it is difficult to replace the damaged parts.

[0004] Therefore, the above problems need to be solved. SUMMARY

[0005] The purpose of the present application is to provide a compression spring lock buckle pop-up separation mechanism for a split-body flying wing layout aircraft, which can effectively limit the relative pitch between the mother aircraft and the sub-aircraft.

[0006] Technical scheme: In order to achieve the above purpose, the present application discloses a compression spring lock buckle pop-up separation mechanism for a split-body flying wing layout aircraft, which comprises a main aircraft connecting rod fixedly connected with a main aircraft, a sub-aircraft nesting rod detachably connected with the main aircraft connecting rod and fixedly connected with a sub-aircraft, and a sub-aircraft separation mechanism fixedly connected with the sub-aircraft and detachably connected with the main aircraft connecting rod.

[0007] The sub-machine separation mechanism comprises a limiting block symmetrically arranged at the tail end of the main machine connecting rod, a guide rail fixedly connected with the sub-aircraft, a central fixed block arranged in the middle of the guide rail, a guide rail slider fixedly connected with the corresponding limiting block and capable of sliding in and out of the guide rail, a guide rod symmetrically arranged at both sides of the central fixed block, a spring arranged on the guide rod and abutting against the limiting block at one end and the central fixed block at the other end, and a constraint assembly for locking the position of the limiting block and compressing the spring.

[0008] The constraint assembly comprises a rudder fixedly arranged on the lower wing surface of the sub-aircraft, a metal rocker arm connected with the output shaft of the rudder, and two bosses arranged on the metal rocker arm, the metal rocker arm is provided with a rudder connecting hole, and the two bosses are arranged at the outer side surfaces of the limiting block and used for clamping the limiting block and compressing the spring.

[0009] Preferably, the main machine connecting rod is symmetrically provided with a front cross rod, a middle cross rod, a rear cross rod and a limiting nesting sleeve, the lower wing surface of the main aircraft is provided with a connecting groove for arranging the front cross rod and the rear cross rod, the rear cross rod of the main machine connecting rod is arranged in the limiting block, and the limiting nesting sleeve of the main machine connecting rod is nested with the sub-machine nesting rod.

[0010] Further, the central fixed block is a concave-convex structure transversely arranged on the guide rail, the top plate of the central fixed block is provided with a first positioning hole for connecting the guide rail, the lower part of the central fixed block is provided with a stop portion for abutting against the spring between the two side plates, and the guide rods are symmetrically arranged at both sides of the stop portion.

[0011] Further, the guide rail is provided with a first mounting hole at the geometric center and a second mounting hole for being fixed to the lower wing surface of the sub-aircraft, and the first mounting hole of the guide rail is fixedly connected with the first positioning hole of the central fixed block through a bolt.

[0012] Preferably, the limiting block comprises a baffle portion for abutting against the spring, a limiting hole arranged on the baffle portion and used for arranging the main machine connecting rod, a guide rod connecting hole arranged on the baffle portion and used for arranging the guide rod, and a connecting portion arranged on the upper part of the baffle portion and used for being fixedly connected with the guide rail slider, and the connecting portion is provided with a first connecting hole for connecting the guide rail slider.

[0013] Further, the guide rail slider is provided with a sliding groove matched with the guide rail and a second connecting hole for connecting the limiting block, and the second connecting hole is fixedly connected with the first connecting hole of the limiting block through a screw.

[0014] Further, the sub-machine nesting rod is a solid cylinder located in the symmetry plane of the sub-machine separation mechanism, wherein a connecting groove for penetrating the sub-machine nesting rod is arranged on the lower wing surface of the sub-aircraft.

[0015] Advantages: compared with the prior art, the present application has the following remarkable advantages: first, the present application uses the sub-machine nesting rod to limit the pitch of the main machine and the sub-machine during the sub-machine separation process, further improving the stability of the combined flight; second, the structure of the sub-machine separation mechanism is compact, improving the effective payload of the aircraft, simple structure, high reliability, easy to install; finally, the present application uses standard parts such as sliding blocks and guide rails, which are easy to replace when damaged, low in manufacturing cost and easy to promote. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a schematic view of the combined mode of the main aircraft and the sub-aircraft in the present application from the top view;

[0017] Figure 2 is a structural schematic view of the main machine connecting rod in the present application;

[0018] Figure 3 is a structural schematic view of the sub-machine separation mechanism in the present application Figure 1 ;

[0019] Figure 4 is a structural schematic view of the guide rail in the present application;

[0020] Figure 5 is a structural schematic view of the guide rail sliding block in the present application;

[0021] Figure 6 is a structural schematic view of the central fixed block in the present application;

[0022] Figure 7 is a structural schematic view of the limiting block in the present application;

[0023] Figure 8 is a structural schematic view of the metal rocker arm in the present application;

[0024] Figure 9 is a connection schematic view of the main machine connecting rod and the sub-machine separation mechanism in the present application Figure 1 ;

[0025] Figure 10 is a connection schematic view of the main machine connecting rod and the sub-machine separation mechanism in the present application Figure 2 ;

[0026] Figure 11 is a structural schematic view of the sub-machine separation mechanism in the present application Figure 2 . DETAILED DESCRIPTION

[0027] The technical solution of the present invention will be further described below with reference to the accompanying drawings.

[0028] like Figure 1 As shown, the present invention provides a compression spring lock spring-release separation mechanism for a detachable flying wing layout aircraft, which is suitable for separating a main aircraft 3 and a sub-aircraft 4. The compression spring lock spring-release separation mechanism for a detachable flying wing layout aircraft includes a main aircraft connecting rod 1, a sub-aircraft separation mechanism 2 and a sub-aircraft nesting rod 5. One end of the main aircraft connecting rod 1 is fixedly connected to the lower wing surface of the main aircraft, and the other end of the main aircraft connecting rod 1 is detachably connected to the sub-aircraft separation mechanism 2. The limiting nesting cylinder 104 of the main aircraft connecting rod 1 is detachably connected to the sub-aircraft nesting rod 5; the sub-aircraft nesting rod 5 is fixedly connected to the lower wing surface of the sub-aircraft; the sub-aircraft separation mechanism 2 is fixedly connected to the lower wing surface of the sub-aircraft; wherein the main aircraft connecting rod 1 and the sub-aircraft separation mechanism 2 can be symmetrically arranged in two groups on the left and right. During the flight, the sub-aircraft separation mechanism 2 and the sub-aircraft nesting rod 5 are successively separated from the main aircraft connecting rod 1 to realize the separation of the main aircraft 3 and the sub-aircraft 4. As shown Figure 2 As shown, the main machine connecting rod 1 is symmetrically provided with a front cross bar 101, a middle cross bar 102, a rear cross bar 103 and a limiting nesting tube 104, wherein a connecting groove for passing the front cross bar and the rear cross bar is opened on the lower wing surface of the main aircraft 3, the rear cross bar 103 of the main machine connecting rod 1 is passed through the limiting block 201 of the sub-machine separation mechanism 2, and the limiting nesting tube 104 of the main machine connecting rod 1 is nested in the sub-machine nesting rod 5.

[0029] like Figure 3 and Figure 11 As shown, the slave unit separation mechanism 2 includes a limit block 201, a guide rail 202, a central fixed block 203, a guide rail slider 204, a guide rod 205, a spring 206 and a constraint component, and the constraint component includes a servo 207, a metal rocker arm 208 and a boss 209. Figure 7As shown, the two limit blocks 201 are symmetrically arranged on the tail end of the main machine connecting rod, and the limit block 201 comprises a baffle part 214, a limiting hole 215, a guide rod connecting hole 216 and a connecting part 217. The baffle part 214 and the connecting part 217 are integrally formed, the baffle part 214 is used for abutting against the spring 206, the limiting hole 215 is arranged on the upper part of the baffle part 214, and the limiting hole 215 is used for penetrating the main machine connecting rod 1. The guide rod connecting hole 216 is arranged on the lower part of the baffle part 214, and the guide rod connecting hole 216 is used for penetrating the guide rod 205. The connecting part 217 is arranged on the upper part of the baffle part, and the connecting part 217 is a horizontally arranged plate. The connecting part 217 is used for being fixed with the guide rail sliding block 204. A first connecting hole 218 for connecting the guide rail sliding block 204 is arranged on the connecting part 217. The upper surface of the connecting part 217 is in close contact with the lower surface of the guide rail sliding block 204. The guide rail sliding block 204 is provided with a sliding groove 219 and a second connecting hole 220. The cross section of the guide rail sliding block 204 is a groove type structure. The guide rail 202 is arranged in the sliding groove 219 of the guide rail sliding block 204, and the guide rail sliding block 204 can slide in and out of the guide rail 202. Figure 5 As shown, the second connecting hole 220 of the guide rail sliding block 204 is fixedly connected with the first connecting hole 218 of the limit block 201 through a screw. When the guide rail sliding block 204 slides in and out of the guide rail 202, the limit block 201 moves along the guide rail 202. Figure 4 As shown, 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 fixed block 203 through a bolt. A plurality of second mounting holes 213 are uniformly arranged on the guide rail 202, and the second mounting holes 213 are fixedly connected with the lower wing surface of the sub-aircraft through a bolt, so as to fix the guide rail 202 on the lower wing surface of the sub-aircraft. Figure 6 As shown, the central fixed block 203 is a reverse concave structure which spans the guide rail 202. The central fixed block 203 is arranged in the middle of the guide rail. The top plate of the central fixed block 203 is provided with a first positioning hole 210 for connecting the guide rail. The guide rail 202 penetrates the central fixed block 203, and the first positioning hole 210 of the central fixed block 203 is fixedly connected with the first mounting hole 212 of the guide rail 202 through a bolt. The lower part of the central fixed block 203 is provided with a stop part 211 between the two side plates, which is used for abutting against the spring. The guide rods 205 are symmetrically arranged on the two sides of the stop part 211. The spring 206 penetrates the guide rod 205. One end of the spring 206 abuts against the limit block, and the other end of the spring 206 abuts against the central fixed block. Figure 8As shown, the constraint assembly is used to lock the position of the limiting block and compress 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 output shaft of the steering engine, the steering engine connecting hole 221 is opened on the metal rocker arm 208, and the two bosses 209 are located on the metal rocker arm, the bosses 209 are respectively located at the outer side of the limiting block 201, and are used to clamp the limiting block 201 and compress the spring. In the initial state, the two bosses 209 are respectively correspondingly abutted against the outer side of the two limiting blocks 201 and compress the spring 206 together with the baffle part of the limiting block, so as to guarantee that the limiting block 201 is arranged on the main machine connecting rod 1; the steering engine 207 is started to drive the metal rocker arm 208 to rotate, the boss 209 rotates together with the metal rocker arm 208, the boss is separated from the outer side of the limiting block 201, the limiting constraint of the limiting block 201 is released, the limiting block 201 moves together with the guide rail sliding block 204 to the outer side of the guide rail 202 under the rebound force of the spring 206, the limiting block 201 is separated from the tail end of the main machine connecting rod 1, so that the sub-aircraft 4 moves backward, after moving to a certain distance, the sub-machine nesting rod 5 is separated from the limiting nesting cylinder 104 of the main machine connecting rod 1, and the sub-aircraft 4 is separated from the main aircraft 3, like Figure 9 and Figure 10 As shown.

Claims

1. A compression spring lock snap-open separation mechanism for a detachable flying wing aircraft, characterized in that: The invention comprises a main aircraft connecting rod (1) fixedly connected to a main aircraft (3), a sub-aircraft nesting rod (5) fixedly connected to a sub-aircraft (4) and detachably connected to the main aircraft connecting rod (1), and a sub-aircraft separation mechanism (2) fixedly connected to the sub-aircraft (4) and detachably connected to the main aircraft connecting rod (1). The sub-machine separation mechanism (2) comprises a limit block (201) symmetrically arranged on the left and right sides of the rear end of the main machine connecting rod, a guide rail (202) fixedly connected to the sub-aircraft, a central fixed block (203) arranged in the middle of the guide rail, a guide rail slider (204) fixedly connected to the corresponding limit block and capable of sliding along the guide rail, a guide rod (205) symmetrically arranged on both sides of the central fixed block, a spring (206) arranged on the guide rod with one end abutting against the limit block and the other end abutting against the central fixed block, and a constraint component for locking the position of the limit block and compressing the spring, the constraint component releases the limit constraint on the limit block, and the limit block moves toward the outside of the guide rail together with the guide rail slider under the action of the rebound force of the spring, and the limit block is separated from the rear end of the main machine connecting rod. The sub-aircraft moves backward, and after moving to a certain distance, the sub-aircraft nesting rod is separated from the main aircraft connecting rod, and finally the sub-aircraft is separated from the main aircraft; the constraint component includes a steering gear (207) fixed on the lower wing surface of the sub-aircraft, a metal rocker arm (208) connected to the steering gear output shaft, and two bosses (209) located on the metal rocker arm, the metal rocker arm (208) is provided with a steering gear connection hole (221), the bosses (209) are respectively located on the outer side surface of the limit block (201), and are used to clamp the limit block (201) and compress the spring. When the steering gear (207) is started, the metal rocker arm (208) is driven to rotate, and the bosses (209) are separated from the outer side surface of the limit block (201), thereby releasing the limit constraint of the limit block (201).

2. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 1, characterized in that: The main machine connecting rod (1) is symmetrically provided with a front crossbar (101), a middle crossbar (102), a rear crossbar (103) and a position-limiting nesting tube (104), wherein a connecting groove for passing the front crossbar and the rear crossbar is opened on the lower wing surface of the main aircraft (3), the rear crossbar (103) of the main machine connecting rod (1) is passed through the position-limiting block (201), and the position-limiting nesting tube (104) of the main machine connecting rod (1) is nested and connected with the sub-machine nesting rod (5).

3. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 1, characterized in that: The central fixing block (203) is an inverted concave structure spanning the guide rail (202). A first positioning hole (210) for connecting to the guide rail is provided on the upper surface of the top plate of the central fixing block (203). A stopper (211) for abutting against a spring is provided between the lower two side plates of the central fixing block. The guide rods (205) are symmetrically arranged on both sides of the stopper (211).

4. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 3, characterized in that: A first mounting hole (212) and a second mounting hole (213) for fixing to the lower wing surface of the sub-aircraft are provided at the geometric center of the guide rail (202); the first mounting hole (212) of the guide rail and the first positioning hole (210) of the central fixing block are fixedly connected by bolts.

5. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 1, characterized in that: The limit block (201) includes a baffle portion (214) for abutting against a spring, a limit hole (215) formed on the baffle portion and used for passing a main unit connecting rod, a guide rod connecting hole (216) formed on the baffle portion and used for passing a guide rod, and a connecting portion (217) located on an upper portion of the baffle portion and used for fixing to the guide rail slider, wherein the connecting portion (217) is provided with a first connecting hole (218) for connecting to the guide rail slider.

6. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 5, characterized in that: The guide rail slider (204) is provided with a sliding groove (219) adapted to the guide rail and a second connecting hole (220) for connecting to the limit block, wherein the second connecting hole (220) is fixedly connected to the first connecting hole (218) of the limit block (201) by screws.

7. The compression spring lock snap-open separation mechanism for a detachable flying wing aircraft according to claim 1, characterized in that: The sub-machine nesting rod (5) is a solid cylinder and is located within the symmetric plane of the sub-machine separation mechanism, wherein a connection groove for passing the sub-machine nesting rod (5) is provided on the lower wing surface of the sub-aircraft (4).

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