Escape device of single-person aircraft

Abstract

The invention discloses an escape device of a single-person aircraft. The escape device comprises an open type rack, a parachute, a parachute shooting rocket, a bearing device, a separation mechanism and an escape handle. Wherein the open type machine frame is formed by combining a plate, a U-shaped beam, an L-shaped beam, a hoop and a connector assembly, a person is located on the inner side of the U-shaped machine beam, supports on the two sides serve as supporting handrails, the upper portion of the L-shaped beam serves as a placing area of other assemblies, and the connector assembly is locked on a machine body framework through the hoop. In order to solve the problem that an existing parachute is heavy in weight, the invention provides a lifesaving scheme for a single person, the protection function on personnel is emphasized, one-key separation of the personnel and the aircraft is realized through a quick switch when the aircraft breaks down, and the escape personnel stably land under the protection of the parachute. Compared with lifesaving protection for a complete machine system, the escape device only for personnel protection has great advantages in weight and size.

Description

Technical Field

[0001] The invention relates to the field of safety and life-saving of single-person aircraft, in particular to an escape device for single-person aircraft. Background Art

[0002] With the rapid development of low-altitude economy, small manned aircraft are being used more and more widely. In the event of a flight failure, the life-saving protection of the pilot or passengers is becoming more and more important.

[0003] Existing life-saving solutions are generally divided into two types: one is to purchase a multi-power redundant design, which can rely on other powers to achieve a safe emergency landing when one of the powers fails and can be restored to normal operation; the other is a parachute life-saving solution, which uses a ejection parachute to ensure a low-speed landing of the entire aircraft when the entire machine circuit fails and all power stops running.

[0004] The first solution can only be used for life-saving in specific circumstances; the second solution is to save the entire aircraft, and the required parachute bag is large in size and weight, which directly affects the design size and flight performance of the UAV, and has certain restrictions on the flexibility of the operator, which is not conducive to popularization and use. Summary of the invention

[0005] In view of the problem of heavy parachutes in existing solutions, the present invention proposes an escape device for a single-person aircraft. When a failure occurs in the aircraft, a quick switch is used to separate the person from the aircraft with one click, and the escapee lands smoothly under the protection of the parachute.

[0006] The technical solution to achieve the purpose of the present invention is: an escape device for a single-person aircraft, including an open frame, a parachute, a parachute rocket, a carrying device, a disengagement mechanism and an escape handle;

[0007] The open frame is composed of a combination of plates, U-shaped beams, L-shaped beams, hoops and connectors. The personnel are on the inner side of the U-shaped beam, and the two side brackets serve as supporting handrails. The connectors are locked on the crossbeam of the fuselage frame through hoops, and the inner side of the hoops has limit pins; the parachute and the parachute rocket are arranged above the L-shaped beam, and the parachute rocket is connected to the parachute through a first rope; the carrying device is a backboard and a five-point harness led out from the backboard, which is used to tie and fix the personnel, and is fixed to the connector of the open frame through a detachment mechanism; the detachment mechanism is composed of distributed four-point latch mechanisms and an unlocking mechanism, and the unlocking mechanism is composed of a second rope, a plastic tube and a fixed pulley, and the latch mechanism is pulled and displaced by the second rope, and the second rope includes rope one, rope two, rope three, and rope four, and the four ropes are fixed in the plastic tube. The fixed pulley is used to change and limit the traction direction of the second rope. The four ropes converge on the fixing mechanism. The fixing mechanism is composed of a lock tongue, a lock seat and a cover plate. The lock tongue is fixed with a third rope gathered by four pins. The lock tongue rotates around the rotating axis of the lock seat, and the third rope is pulled synchronously to move. The cover plate fixes four plastic tubes; the escape handle is connected to the lock tongue of the fixing mechanism through the safety switch and the handle. When the handle is pulled downward, the third rope drives the lock tongue to rotate; the lock switch is fixed behind the back plate, and there is a hanging ear structure on both sides of the internal groove, which is connected to the hanging ear structure on the latch mechanism through two micro springs. When the connector is inserted into the lock in sequence, the latch is stuck in the connector groove to form an automatic reset mechanism. When the disengagement mechanism receives the command, the energy storage compression spring between the disengagement mechanism and the connector causes the connector to pop out to prevent the lock from getting stuck.

[0008] Compared with the prior art, the present invention has the following significant advantages: the present invention proposes an escape device for a single-person aircraft, which is compact and highly safe, and at the same time has the characteristics of flexible operation; compared with the life-saving protection of the entire aircraft system, the protection only for personnel has great advantages in weight and volume of the life-saving device; the present invention adopts a wearable body structure, combined with a high-precision mechanical separation mechanism, to achieve human-machine separation, protect personnel safety, and realize the convenience of personnel separation, low control difficulty, and fast response speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 It is a composition diagram of the escape device of the single-person aircraft of the present invention.

[0010] Figure 2 The figure is a system diagram of the escape device of the single-person aircraft of the present invention.

[0011] Figure 3 This is a structural diagram of an open frame of the present invention.

[0012] Figure 4 It is a structural diagram of the safety life-saving system of the present invention.

[0013] Figure 5It is a structural diagram of the carrying device of the present invention.

[0014] Figure 6 It is a schematic diagram of the disengagement mechanism of the present invention.

[0015] Figure 7 It is a schematic diagram of the fixing mechanism of the present invention.

[0016] Figure 8 It is the internal structure diagram of the fixing mechanism of the present invention.

[0017] Fig. 9 It is a structural diagram of the escape handle of the present invention.

[0018] Fig.10 It is a schematic diagram of the lock disengagement effect of the disengagement mechanism of the present invention, wherein the left figure is a schematic diagram of the internal structure of the lock of the present invention, and the right figure is a schematic diagram of the effect of the lock being released.

[0019] Fig.11 Schematic diagram of the latch mechanism.

[0020] Fig.12 It is a schematic diagram of an embodiment of the present invention. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. Based on the implementation of this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0022] Combination Figures 1 to 12The present invention proposes an escape device for a single-person aircraft, which is mainly composed of an open frame 1, a parachute 2, a parachute rocket 3, a carrying device 4, a detachment mechanism 5 and an escape handle 6. The open frame 1 is composed of a plate 7, a U-shaped beam 8, an L-shaped beam 9, a clamp 10 and a connector 11. The plate 7 is connected to the L-shaped beam 9. The personnel are on the inner side of the U-shaped beam 8. The brackets on both sides serve as support handrails. The area above the L-shaped beam 9 serves as a flight control module placement area. The connector 11 is locked on the aircraft fuselage frame through the clamp 10, and the inner side of the clamp has a limit pin; the parachute 2 and the parachute rocket 3 are arranged above the L-shaped beam 9. The parachute rocket 3 is connected to the parachute 2 through a first rope 12. When a failure occurs, the parachute rocket 3 is launched to drive the parachute to eject into the air; the carrying device 4 is a backboard 13 The five-point harness 14 derived from the backboard can be used to tie and fix the personnel. The personnel are fixed on the chest by a switch 30 and fixed to the connector 11 of the open frame by a detachment mechanism 5. Two straps 15 are extended from the left and right shoulders of the five-point harness 14 and connected to the parachute 2. The detachment mechanism 5 is composed of four distributed latch mechanisms 16 and an unlocking mechanism 17. The unlocking mechanism 17 is composed of a second rope 18, a plastic tube 19 and a fixed pulley 36. The latch mechanism 16 can be pulled and displaced by the second rope 18. The second rope 18 includes rope 1, rope 2, rope 3 and rope 4. , the four ropes are fixed in position and direction in the plastic tube 19, the fixed pulley 36 is used to change and limit the pulling direction of the second rope, the four ropes converge on the fixing mechanism 20 of the unlocking mechanism 17, the fixing mechanism 20 is composed of a lock tongue 21, a lock seat 22 and a cover plate 24, the third rope 29 of the four latch mechanisms is fixed on the lock tongue 21, the lock tongue 21 can rotate around the rotation axis 23 of the lock seat 22, and synchronously pull the third rope 29 to move, the cover plate 24 is used to fix the four plastic tubes 19; the four latch mechanisms are fixed to the structural member 24, and the wire clips 25 and 26 gather the ropes at the left shoulder handle; the escape handle 6 is arranged at The left shoulder strap is connected to the locking tongue 21 of the fixing mechanism through a safety switch 27 and a handle 28. Pulling the handle 28 downwards, the third rope 29 can drive the locking tongue to rotate; the lock switch 31 is locked at the back of the back plate by four screws, and there are ear structures 32 on both sides of the internal groove, which are connected to the ear structure 35 on the latch mechanism 16 through two micro springs 33. When the connector is inserted into the lock in sequence, the latch is stuck in the connector groove to form an automatic reset mechanism. When the disengagement mechanism 5 receives the command, the energy storage compression spring 34 between the disengagement mechanism 5 and the connector 11 causes the connector to pop out to prevent the lock from getting stuck.

[0023] When the aircraft fails and cannot continue to operate normally, the pilot's flight helmet will immediately send out voice and vibration reminders for emergency rescue. At this time, the pilot pulls the escape handle, and the escape handle pulls the lock tongue of the unlocking mechanism through the third rope to rotate. The lock tongue drives the escape ropes 1, 2, 3, and 4 to move together. The movement is transmitted to the four pins of the escape mechanism to move synchronously in the unlocking direction. The escape mechanism is fully opened, the connection between the backpack and the body is in contact, and the backpack and the pilot are separated from the aircraft; at the same time, the parachute rocket receives the command of the rescue handle and ejects, driving the parachute to take off and unfold. The pilot and the backpack are connected to the parachute through straps, and slowly descend under the resistance of the parachute and land safely.

[0024] The above description is only a specific implementation of the present invention, but the protection scope of the present invention is not limited thereto. Any person familiar with the technology can understand and think of any changes or substitutions within the technical scope disclosed by the present invention, which should be included in the scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An escape device for a single-person aircraft, characterized in that: It comprises an open frame (1), a parachute (2), a parachute rocket (3), a carrying device (4), a separation mechanism (5) and an escape handle (6); The open frame (1) is composed of a plate (7), a U-shaped beam (8), an L-shaped beam (9), a hoop (10) and a connector (11). A person is located on the inner side of the U-shaped beam, and the brackets on both sides serve as support handrails. The connector (11) is locked on the cross beam of the fuselage frame through the hoop (10), and the inner side of the hoop has a limit pin; the parachute (2) and the parachute rocket (3) are arranged above the L-shaped beam (9), and the parachute rocket (3) is connected to the parachute (2) through a first rope (12); the carrying device (4) is a backboard (13) and a cable drawn from the backboard. The five-point harness (14) is used to tie and fix a person, and is fixed to a connector (11) of an open frame through a disengagement mechanism (5); the disengagement mechanism (5) is composed of four distributed latch mechanisms (16) and an unlocking mechanism (17); the unlocking mechanism (17) is composed of a second rope (18), a plastic tube (19) and a fixed pulley (36); the latch mechanism (16) is pulled and displaced by the second rope (18); the second rope (18) includes rope 1, rope 2, rope 3 and rope 4; the four ropes are fixed in position in the plastic tube (19). The fixed pulley (36) is used to change and limit the pulling direction of the second rope. The four ropes converge on the fixing mechanism (20). The fixing mechanism (20) is composed of a lock tongue (21), a lock seat (22) and a cover plate (24). The lock tongue (21) is fixed with a third rope (29) gathered by four bolts. The lock tongue (21) rotates around the rotation axis (23) of the lock seat (22) to synchronously pull the third rope (29) to move. The cover plate (24) is used to fix four plastic pipes (19); the escape handle (6) is connected to the fixing mechanism through a safety switch (27) and a handle (28). The lock tongue (21) is connected to the lock tongue (21), and the handle is pulled downward, and the third rope (29) drives the lock tongue (21) to rotate; the lock switch (31) is fixed at the rear of the back plate, and the two sides of the internal groove are respectively provided with a first hanging ear structure (32), which is connected to the second hanging ear structure (35) on the latch mechanism (16) through two micro springs (33); when the connector is inserted into the lock buckle in sequence, the latch is inserted into the connector groove to form an automatic reset mechanism; when the disengagement mechanism (5) receives the command, the energy storage compression spring (34) between the disengagement mechanism (5) and the connector (11) causes the connector to pop out, thereby preventing the lock buckle from being stuck.

2. The escape device for a single-person aircraft according to claim 1, characterized in that: The area above the L-shaped beam (9) serves as a flight control module placement area.

3. The escape device for a single-person aircraft according to claim 1, characterized in that: Four latches are fixed to the structural member (24), and the wire clip gathers the rope at the left shoulder handle.

4. The escape device for a single-person aircraft according to claim 1, characterized in that: The escape handle (6) is arranged at the left shoulder strap position.

5. The escape device for a single-person aircraft according to claim 1, characterized in that: The lock switch (31) is locked behind the back plate by four screws.

6. The escape device for a single-person aircraft according to claim 1, characterized in that: The five-point harness (14) is fixed via a switch piece (30) in front of the chest.

7. The escape device for a single-person aircraft according to claim 1, characterized in that: When a failure occurs, the parachute rocket (3) is launched to drive the parachute (2) to be ejected into the air.

8. The escape device for a single-person aircraft according to claim 1, characterized in that: Two straps (15) extend from the left and right shoulder positions of the five-point harness (14) and are connected to the parachute (2).

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