CN116176840A - Detachable snap-lock pop-up separation mechanism for aircraft with separable flying wing layout - Google Patents

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

Detachable snap-lock pop-up separation mechanism for aircraft with separable flying wing layout

technical field

The invention relates to a separation mechanism for a main aircraft and a sub-aircraft, in particular to a spring lock snap-open type separation mechanism for an aircraft with a splitable flying wing layout.

Background technique

The split-type layout is a new type of aircraft layout scheme, which can give full play to the advantages of the split-type aircraft assembly and its individual, and integrate the technology of multi-UAV cluster flight control into it, further improving the multi-task execution capability of the aircraft. Greatly expand the use of aircraft.

The split combination of the aircraft involves the design of separate combination devices and controls, and requires a powerful flight control program as support. During the separation process of the lead aircraft and the slave aircraft, due to complex unsteady airflow interference, physical collisions between aircraft may occur, thus affecting the safety of separation. The previous application (2022106735928) discloses a detachable flying wing layout unmanned aerial vehicle. In order to ensure the stable connection of the combined aircraft, the previous sub-machine separation mechanism has too many arrangements, many parts and is not compact enough. As a result, the mass is too heavy, which reduces the payload of the aircraft; in addition, there is still a high degree of static uncertainty. If the manufacturing accuracy cannot reach the specified tolerance, it will cause difficulty in installation; the guide rail slider is made of non-standard parts. Problems such as difficulty in replacement.

Therefore, urgently need to solve the above problems.

Contents of the invention

Purpose of the invention: The purpose of the present invention is to provide a spring lock snap-open type separation mechanism for an aircraft with a separable flying wing layout that can effectively limit the relative pitch between the lead plane and the slave plane.

Technical solution: In order to achieve the above objectives, the present invention discloses a spring lock snap-open type separation mechanism for an aircraft with a separable flying wing layout. The sub-machine nesting rod that is detachably connected and fixedly connected with the sub-aircraft, and the sub-machine separation mechanism that is fixedly connected with the sub-aircraft and is detachably connected with the connecting rod of the main machine.

The sub-machine separation mechanism includes a left-right symmetrical limit block installed at the tail end of the connecting rod of the main engine, a guide rail fixedly connected with the sub-aircraft, and a central fixed block in the middle of the guide rail, which is fixedly connected with the corresponding limit block and can be moved along the The guide rail slide block that slides inside and outside the guide rail is symmetrically arranged on the guide rods on both sides of the central fixed block, the spring that is threaded on the guide rod and abuts on the limit block at one end, and abuts on the central fixed block at the other end, and uses The constraining component locks the position of the limit block and compresses the spring, and the constraining component releases the limit constraint on the limit block. The tail end of the connecting rod of the main machine is separated, so that the sub-aircraft moves backward. After moving to a certain distance, the nesting rod of the sub-machine is separated from the connecting rod of the main machine, and finally the sub-aircraft is separated from the main aircraft.

Wherein, the constraint assembly includes a steering gear fixed on the lower wing surface of the sub-aircraft, a metal rocker arm connected to the output shaft of the steering gear, and two bosses on the metal rocker arm. The metal rocker arm is provided with a steering gear Connecting holes, the bosses are respectively located on the outer side of the limit block, used to clamp the limit block and compress the spring, the servo starts, drives the metal rocker to rotate, the boss is separated from the outer side of the limit block, and the limit is released Block constraints.

Preferably, the connecting rod of the main engine is symmetrically provided with a front cross bar, a middle cross bar, a rear cross bar and a limiting sleeve, wherein the lower wing of the main aircraft is provided with a cross bar for passing through the front cross bar and the rear cross bar. The connecting groove of the connecting rod, the rear cross bar of the connecting rod of the main frame is set on the limit block, and the nesting sleeve of the connecting rod of the main frame is nested and connected with the nesting rod of the sub-machine.

Furthermore, the central fixing block is an inverted concave structure that straddles the guide rails. The upper surface of the top plate of the central fixing block is provided with a first positioning hole for connecting the guide rails. Abutting against the stop portion of the spring, the guide rods are symmetrically arranged on both sides of the stop portion.

Further, the geometric center of the guide rail is provided with a first installation hole and a second installation hole for fixing on the lower wing surface of the sub-aircraft, and the first installation hole of the guide rail and the first positioning hole of the central fixing block are fixed by bolts. even.

Preferably, the limit block includes a baffle part for abutting against the spring, a limit hole opened on the baffle part and used for passing through the connecting rod of the main engine, opened on the baffle part and used for passing through the guide The guide rod connection hole of the rod and the connection part located on the upper part of the baffle part and used for fixing the guide rail slider are provided on the connection part with a first connection hole for connecting the guide rail slider.

Furthermore, the guide rail slider is provided with a chute suitable for the guide rail and a second connection hole for connecting the limit block, wherein the second connection hole is fixedly connected with the first connection hole of the limit block by screws .

Further, the sub-machine nesting rod is a solid cylinder, located in the symmetry plane of the sub-machine separation mechanism, wherein the lower wing of the sub-aircraft is provided with a connecting groove for passing through the sub-machine nesting rod.

Beneficial effects: Compared with the prior art, the present invention has the following significant advantages: firstly, the present invention uses the sub-machine nesting rod to realize the pitch limitation of the main machine and the sub-machine during the separation process of the sub-machine, and further improves the stability of the combined flight; secondly, the present invention The sub-machine separation mechanism of the invention has a compact structure, improves the payload of the aircraft, has a simple structure, high reliability, and is easy to install; finally, standard parts such as sliders and guide rails are used in the present invention, which are easy to replace after damage, and the manufacturing cost is low, which is convenient for popularization .

Description of drawings

Fig. 1 is a top view schematic diagram of the combination mode of the main aircraft and the sub-aircraft in the present invention;

Fig. 2 is the structural representation of host connecting rod among the present invention;

Fig. 3 is a structural schematic diagram 1 of the neutron machine separation mechanism of the present invention;

Fig. 4 is the structural representation of guide rail among the present invention;

Fig. 5 is the structural representation of guide rail slider in the present invention;

Fig. 6 is the structural representation of central fixed block among the present invention;

Fig. 7 is a schematic structural view of a limiting block in the present invention;

Fig. 8 is a structural schematic diagram of a metal rocker arm in the present invention;

Fig. 9 is a schematic diagram of the connection between the connecting rod of the main machine and the separation mechanism of the sub-machine in the present invention;

Fig. 10 is a second schematic diagram of the connection between the connecting rod of the host machine and the separation mechanism of the slave machine in the present invention;

Fig. 11 is the second structural schematic diagram of the neutron machine separation mechanism of the present invention.

Detailed ways

The technical solution of the present invention will be further described below in conjunction with the accompanying drawings.

As shown in Fig. 1 , a spring lock snap-open separation mechanism of the present invention is suitable for the separation of the main aircraft 3 and the sub-aircraft 4, and a detachable flying wing layout aircraft The spring lock snap-open type separation mechanism of the aircraft includes the connecting rod 1 of the main machine, the separating mechanism 2 of the slave machine and the nesting rod 5 of the slave machine. One end of the connecting rod 1 of the main machine is fixedly connected with the lower wing of the main aircraft, and the other end of the connecting rod 1 of the main machine It is detachably connected with the sub-machine separation mechanism 2, and the limit nesting cylinder 104 of the main machine connecting rod 1 is detachably connected with the sub-machine nesting rod 5; the sub-machine nesting rod 5 is fixedly connected with the lower wing of the sub-aircraft; the sub-machine is separated The mechanism 2 is fixedly connected to the lower wing of the sub-aircraft; wherein the connecting rod 1 of the main engine and the separation mechanism 2 of the sub-machine can be respectively arranged in two groups symmetrically. During the flight, the sub-machine separation mechanism 2 and the sub-machine nesting rod 5 are separated from the main machine connecting rod 1 successively to realize the separation of the main aircraft 3 and the sub-aircraft 4 . As shown in Figure 2, the front cross bar 101, the middle cross bar 102, the rear cross bar 103 and the limit nesting sleeve 104 are arranged symmetrically on the connecting rod 1 of the main engine, wherein the lower wing surface of the main aircraft 3 is provided with a The connecting groove of the front crossbar and the rear crossbar, the rear crossbar 103 of the connecting rod 1 of the main machine is set on the limit block 201 of the separation mechanism 2 of the slave machine, and the limit nesting cylinder 104 of the connecting rod 1 of the main machine is nested in the slave machine Nest rod 5.

As shown in Fig. 3 and Fig. 11, the sub-machine 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 restraint assembly, and the restraint assembly includes a steering gear 207, Metal rocker arm 208 and boss 209 . As shown in Figure 7, two limit blocks 201 are arranged symmetrically on the rear end of the host connecting rod. The limit block 201 includes a baffle part 214, a limit hole 215, a guide rod connection hole 216 and a connecting part 217. The baffle The part 214 and the connecting part 217 are integrally formed. The baffle part 214 is used to abut against the spring 206. The limit hole 215 is opened on the upper part of the baffle part 214. The limit hole 215 is used to pass through the host connecting rod 1 and the guide rod. The connecting hole 216 is opened at the bottom of the baffle plate part 214, the guide rod connecting hole 216 is used to pass through the guide rod 205, the connecting part 217 is located at the upper part of the baffle plate part, and the connecting part 217 is a horizontal plate, and the connecting part 217 is used to connect with the baffle plate part. The guide rail slider 204 is fixed, and the connecting portion 217 is provided with a first connecting hole 218 for connecting the guide rail slider 204 , and the upper surface of the connecting portion 217 is attached to the lower surface of the guide rail slider 204 . The guide rail slider 204 is provided with a chute 219 and a second connecting hole 220, the cross section of the guide rail slider 204 is a groove structure, the guide rail 202 is located in the chute 219 of the guide rail slider 204, and the guide rail slider 204 can move along the guide rail. 202 slides inside and out. As shown in Figure 5, the second connection hole 220 of the guide rail slider 204 is fixedly connected with the first connection hole 218 of the limit block 201 by screws, and when the guide rail slider 204 slides inside and outside along the guide rail 202, it drives the limit block 201 along the guide rail. 202 move together. As shown in Figure 4, a first installation hole 212 and a second installation hole 213 are provided on the guide rail 202, the first installation hole 212 is located at the geometric center of the guide rail 202, the first installation hole 212 of the guide rail 202 and the central fixed block 203 The first positioning holes 210 are fixedly connected by bolts. A plurality of 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 of the sub-aircraft by bolts for fixing the guide rail 202 on the lower wing of the sub-aircraft. As shown in Figure 6, the central fixed block 203 is an inverted concave structure across the guide rail 202, the central fixed block 203 is installed in the middle of the guide rail, and the upper surface of the top plate of the central fixed block 203 is provided with a first positioning hole for connecting the guide rail 210 , the guide rail 202 passes through the central fixing block 203 , and the first positioning hole 210 of the central fixing block 203 is connected with the first installation hole 212 of the guide rail 202 through bolts. A stopper 211 for abutting against the spring is arranged between the lower side plates of the central fixed block 203, the guide rod 205 is symmetrically arranged on both sides of the stopper 211, the spring 206 is passed through the guide rod 205, and the spring 206 One end abuts against the limiting block, and the other end of the spring 206 abuts against the central fixing block. As shown in Figure 8, the constraint assembly is used to lock the position of the limit block and compress the spring. The steering gear 207 is fixed on the lower wing surface of the sub-aircraft, and the metal rocker arm 208 is connected with the output shaft of the steering gear. The steering gear connection hole 221 and two bosses 209 are located on the metal rocker arm. The bosses 209 are respectively located on the outer side of the limiting block 201 for clamping the limiting block 201 and compressing the spring. In the initial state, the two bosses 209 respectively abut against the outer sides of the two limit blocks 201 and compress the spring 206 together with the baffles of the limit blocks, so as to ensure that the limit block 201 is installed on the connecting rod 1 of the main engine; Machine 207 starts, and drives metal rocker arm 208 to rotate, and boss 209 rotates together with metal rocker arm 208, and boss breaks away from the outer side of limit block 201, and the limit restriction of limit block 201 is released, and limit block 201 is in spring Under the action of the rebound force of 206, the outer side of the guide rail 202 is moved together with the guide rail slider 204, and the limit block 201 is separated from the tail end of the main connecting rod 1, so that the sub-aircraft 4 moves backward. After moving to a certain distance, the sub-machine The nesting rod 5 is separated from the limiting nesting cylinder 104 of the connecting rod 1 of the main engine, and the sub-aircraft 4 is separated from the main aircraft 3, as shown in FIGS. 9 and 10 .

Claims (8)

1. A spring lock snap-open type separation mechanism for a split-body flying-wing layout aircraft is characterized in that it comprises a main engine connecting rod (1) fixedly connected to the main aircraft (3), and a sub-aircraft (4) ) is fixedly connected to the sub-machine nesting rod (5) that is detachably connected to the main connecting rod (1), and the sub-machine separation mechanism (2) that is fixedly connected to the sub-aircraft (4) and is detachably connected to the main connecting rod (1) , The sub-machine separation mechanism (2) includes a limit block (201) symmetrically threaded at the tail end of the main machine connecting rod, a guide rail (202) fixedly connected with the sub-aircraft, and a central fixed block (203) threaded in the middle of the guide rail. , the guide rail slider (204), which is fixedly connected with the corresponding limit block and can slide inside and outside the guide rail, and the guide rods (205), which are symmetrically arranged on both sides of the central fixed block, are threaded on the guide rod and one end abuts against the limit On the position block, the other end abuts against the spring (206) on the central fixed block, and the constraint assembly for locking the position of the limit block and compressing the spring, the constraint assembly releases the limit constraint on the limit block, and the limit block is at Under the elastic force of the spring, it moves to the outside of the guide rail together with the slide block of the guide rail, and the limit block is separated from the tail end of the connecting rod of the main machine, so that the sub-aircraft moves backward. After moving to a certain distance, the sub-machine nesting rod and the main machine The connecting rods are separated, and finally the sub-aircraft is separated from the main aircraft. 2. The detachable spring lock snap-open type separation mechanism for an aircraft with a separable flying wing layout according to claim 1, characterized in that: the restraint assembly includes a steering gear ( 207), the metal rocking arm (208) that links to each other with the output shaft of the steering gear and two bosses (209) that are positioned on the metal rocking arm, offer the steering gear connection hole (221) on the metal rocking arm (208), the Bosses (209) are respectively located at the outer surfaces of the limit block (201), and are used to clamp the limit block (201) and compress the spring. When the steering gear (207) starts, it drives the metal rocker arm (208) to rotate, and the bosses (209) disengage from the outer surface of the limiting block (201), and release the limiting constraint of the limiting block (201). 3. The spring-lock snap-open type separation mechanism for an aircraft with a separable flying wing layout according to claim 1, characterized in that: the connecting rod (1) of the main engine is symmetrically provided with a front cross bar (101 ), the middle cross bar (102), the rear cross bar (103) and the limit sleeve (104), wherein the lower wing surface of the main aircraft (3) is provided with a connection for passing through the front cross bar and the rear cross bar Groove, the rear cross bar (103) of the connecting rod (1) of the main machine is set on the limit block (201), the nesting sleeve (104) of the connecting rod (1) of the main machine and the nesting rod (5) of the sub-machine Nested joins. 4. The spring-lock snap-open separation mechanism for an aircraft with a separable flying wing layout according to claim 1, characterized in that: the central fixing block (203) is an inverted structure that straddles the guide rail (202). Concave structure, the upper surface of the top plate of the central fixed block (203) is provided with a first positioning hole (210) for connecting the guide rail, and a stopper for abutting against the spring is provided between the lower side plates of the central fixed block ( 211), the guide rods (205) are symmetrically arranged on both sides of the stop portion (211). 5. The detachable separation mechanism for the detachable flying wing layout aircraft according to claim 4, characterized in that: the geometric center of the guide rail (202) is provided with a first mounting hole ( 212) and the second mounting hole (213) that is used to be fixed on the lower wing surface of the sub-aircraft, the first mounting hole (212) of the guide rail and the first positioning hole (210) of the central fixed block are fixedly connected by bolts. 6. The detachable spring lock snap-open separation mechanism for an aircraft with a separable flying wing layout according to claim 1, characterized in that: the limit block (201) includes a baffle for abutting against a spring part (214), the limit hole (215) opened on the baffle part and used to pass through the connecting rod of the main engine, the guide rod connecting hole (216) opened on the baffle part and used to pass through the guide rod, and the The connection part (217) on the upper part of the baffle part is used for fixing the guide rail slider, and the first connection hole (218) for connecting the guide rail slider is opened on the connection part (217). 7. The detachable spring-lock snap-open type separation mechanism for aircraft with separable flying wing layout according to claim 6, characterized in that: said guide rail slider (204) is provided with a The chute (219) and the 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 screws. 8. The spring-lock snap-open separation mechanism for an aircraft with a separable flying wing layout according to claim 1, characterized in that: the sub-machine nesting rod (5) is a solid cylinder, located at the sub-machine In the plane of symmetry of the sub-machine separation mechanism, the lower wing surface of the sub-aircraft (3) is provided with a connecting groove for passing through the sub-machine nesting rod (5).

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