Improved tail cone for changing airplane stall into parachute outlet

Abstract

The invention belongs to the technical field of airplane test flight, and discloses a modified tail cone for changing airplane stall into parachute outlet, which comprises a shell, a support ring group and a parachute cylinder, wherein the supporting ring set comprises a first supporting ring and a second supporting ring, the first supporting ring and the second supporting ring are supported in the shell in a spaced mode, a blocking part is arranged on the first supporting ring to block the tail end of the shell, and an outlet is formed in the blocking part; the umbrella cylinder is obliquely arranged in the shell and penetrates through the first supporting ring and the second supporting ring, part of the umbrella cylinder penetrates out of the outlet, and the edge of the umbrella cylinder and the edge of the outlet are connected with corner pieces. The parachute barrel is obliquely arranged in the shell and penetrates out of the outlet, when the stall-changing-out parachute is opened, resistance of the stall-changing-out parachute is transmitted to the first supporting ring through the parachute cord, the first supporting ring is used for bearing direct loads brought by the stall-changing-out parachute cord, then force is transmitted forwards through the shell and the second supporting ring, and the influence on pneumatics can be reduced.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft flight test, in particular to a tail cone modified with an aircraft stall recovery parachute. Background Art

[0002] Stall test flight is the precondition for many other flight test subjects of the aircraft, and because the stall test flight subject belongs to the Class I high-risk subject, it has the characteristics of high risk, high comprehensiveness, and high flight test technology difficulty. In order to ensure flight safety, it is usually necessary to install a stall recovery parachute to prevent the aircraft from entering a deep stall and being unable to recover through self-adjustment. At this time, it is necessary to use the stall recovery parachute to open and give the aircraft a nose-down moment to recover the aircraft from the stall state and return to normal.

[0003] The stall recovery parachute modification generally involves adding a stall recovery parachute device to the tail of the aircraft. Modification of the normal aircraft configuration is bound to affect the normal distribution of the original structural functions, and usually has a significant impact on the aircraft's aerodynamics, affecting other test flight subjects. Summary of the invention

[0004] The purpose of the present invention is to provide a tail cone modified with a parachute for recovering from stall of an aircraft, which has a relatively reasonable design, has a relatively small influence on the aerodynamics of the aircraft, and reduces the influence on other flight test subjects.

[0005] To achieve this object, the present invention adopts the following technical solutions:

[0006] Aircraft stall recovery parachute modification tail cone, including:

[0007] shell;

[0008] A support ring assembly, the support ring assembly comprising a first support ring and a second support ring, the first support ring and the second support ring are supported in the housing at intervals, the first support ring is provided with a blocking portion to block the rear end of the housing, and the blocking portion is provided with an outlet;

[0009] An umbrella tube is tiltedly arranged in the shell, the umbrella tube is passed through the first support ring and the second support ring, a part of the umbrella tube passes through the outlet, and an angle piece is connected to the edge of the umbrella tube and the outlet.

[0010] Preferably, the umbrella tube is arranged obliquely from the bottom of the shell to the top of the shell.

[0011] Preferably, the second support ring is provided with a support portion, the support portion extends along the inner side of the second support ring toward the central axis of the outer shell, the support portion is provided with a through groove, and the umbrella tube abuts against the through groove so as to be supported by the support portion.

[0012] Preferably, an exhaust port is provided on the side of the shell, and an exhaust pipe is plugged into the exhaust port.

[0013] Preferably, the exhaust pipe is a bent pipe, the exhaust pipe is passed through the second support ring, the second support ring is provided with at least one fixed support, and the exhaust pipe is fixed on the fixed support.

[0014] Preferably, a heat insulation structure is further provided, the heat insulation structure comprises an umbrella tube heat insulation layer, and the umbrella tube heat insulation layer is provided on the inner side of the umbrella tube.

[0015] Preferably, the thermal insulation structure further comprises a supporting thermal insulation layer, and the supporting thermal insulation layer is arranged on a side of the sealing portion facing the inner side of the shell.

[0016] Preferably, a side portion of the housing is provided with an inspection port, and the inspection port is arranged opposite to the exhaust port.

[0017] Preferably, the inspection port is located between the first support ring and the second support ring, and the inspection port is provided with an inspection cover that opens outward.

[0018] Preferably, the outer shell includes two side panel walls, the side portions of the two side panel walls are connected to form a truncated cone shape, and a wall panel docking piece is provided between the connection points of the side panel walls so as to enable connection through the wall panel docking piece.

[0019] Beneficial effects of the present invention:

[0020] The parachute tube is tilted in the outer shell and passes through the exit. When the stall recovery parachute is opened, the resistance of the stall recovery parachute is transmitted to the first support ring through the parachute rope. The first support ring is used to bear the direct load brought by the stall recovery parachute rope, and then transmits force forward through the outer shell and the second support ring, which can reduce the impact on aerodynamics, and the setting of the corner piece can further reduce the aerodynamic impact; reducing the impact on other test flight subjects. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of a tail cone modified with a stall recovery parachute of an aircraft according to the present invention;

[0022] Figure 2 It is a schematic diagram of one viewing angle of the aircraft stall recovery parachute of the present invention after the tail cone is modified and the outer shell is removed;

[0023] Figure 3 It is a schematic diagram of another perspective of the aircraft stall recovery parachute of the present invention, in which the tail cone is modified and the outer shell is removed;

[0024] Figure 4 It is a schematic diagram of the aircraft stall recovery parachute modification tail cone of the present invention showing the inspection port and the exhaust port;

[0025] Figure 5The present invention is a schematic diagram of a display inspection cover for a tail cone of an aircraft stall recovery parachute modification.

[0026] In the figure:

[0027] 1. Outer shell; 11. Side panel wall; 12. Wall panel docking piece; 2. Support ring assembly; 21. First support ring; 22. Second support ring; 23. Support portion; 24. Corner piece; 25. Sealing portion; 3. Umbrella tube; 4. Exhaust port; 5. Exhaust pipe; 6. Fixed support; 7. Inspection port; 8. Inspection cover. DETAILED DESCRIPTION

[0028] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0029] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0031] In the description of this embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operate in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0032] like Figures 1 to 5As shown, the present embodiment provides a modified tail cone for an aircraft stall recovery parachute, which comprises an outer shell 1, a support ring group 2 and an umbrella tube 3; wherein the support ring group 2 comprises a first support ring 21 and a second support ring 22, the first support ring 21 and the second support ring 22 are supported in the outer shell 1 at intervals, a blocking portion 25 is provided on the first support ring 21 to block the rear end of the outer shell 1, and an outlet is provided on the blocking portion 25; the umbrella tube 3 is obliquely arranged in the outer shell 1, the umbrella tube 3 is penetrated through the first support ring 21 and the second support ring 22, a part of the umbrella tube 3 passes through the outlet, and an angle piece 24 is connected to the edge of the umbrella tube 3 and the outlet.

[0033] The parachute tube 3 is tiltedly arranged in the outer shell 1 and passes through the exit. When the condition for opening the stall recovery parachute is met, the resistance of the stall recovery parachute is transmitted to the first support ring 21 through the parachute rope. The first support ring 21 is used to bear the direct load brought by the stall recovery parachute rope, and then transmits force forward through the outer shell 1 and the second support ring 22, which can reduce the impact on aerodynamics, and the setting of the corner piece 24 can further reduce the aerodynamic impact; reduce the impact on other test flight subjects.

[0034] The present embodiment is described in detail below. Figures 1 to 3 As shown, the tail cone modified for the aircraft stall recovery parachute includes an outer shell 1, which is formed by splicing and enclosing two side panel walls 11, and the side parts of the two side panel walls 11 are connected to form a truncated cone. In this embodiment, after the outer shell 1 is correctly installed on the tail of the aircraft, the end away from the aircraft is defined as the tail end of the outer shell 1, that is, the dome of the truncated cone. In this embodiment, a wall panel docking piece 12 is provided between the connection parts of the side panel walls 11, so that the two side panel walls 11 can be connected through the wall panel docking piece 12. Specifically, the cross-section of the wall panel docking piece 12 is T-shaped, I-shaped or straight-shaped, and there is no specific limitation here, as long as it can connect the two side panel walls 11.

[0035] A support ring group 2 and an umbrella tube 3 are arranged in the outer shell 1, wherein the support ring group 2 includes a first support ring 21 and a second support ring 22, the first support ring 21 and the second support ring 22 support the outer shell 1 at intervals, and the first support ring 21 is arranged at the tail end of the outer shell 1. In addition, the first support ring 21 is provided with a blocking portion 25, so that the tail end of the outer shell 1 can be blocked by the blocking portion 25, and an outlet is arranged on the blocking portion 25. The umbrella tube 3 is tiltedly arranged in the outer shell 1, and is used to place the stall recovery parachute body. Specifically, the umbrella tube 3 is tiltedly arranged from the bottom of the outer shell 1 to the top of the outer shell 1. It can be understood that the bottom of the outer shell 1 and the top of the outer shell 1 here refer to the relative spatial position of the outer shell 1 relative to the aircraft when the outer shell 1 is correctly installed at the tail of the aircraft. The umbrella tube 3 adopts an inclined upward arrangement to provide the required ejection angle for the stall recovery parachute. In this embodiment, the cross-sectional shape of the parachute tube 3 is an intersection of a circle and a rectangle, the upper circular portion is mainly used to store the folded stall recovery parachute body, and the lower rectangular groove is mainly used to store the stall recovery parachute ropes.

[0036] Specifically, the umbrella tube 3 is passed through the first support ring 21 and the second support ring 22, and part of the umbrella tube 3 passes through the outlet. More specifically, the second support ring 22 is provided with a support portion 23, and the support portion 23 extends along the inner side of the second support ring 22 toward the central axis of the outer shell 1, and a through groove is provided on the support portion 23, and the umbrella tube 3 abuts against the through groove so as to be supported by the support portion 23. After the resistance of the stall recovery parachute is transmitted to the first support ring 21 through the parachute rope, the first support ring 21 is used to bear the direct load brought by the stall recovery parachute rope, and then transmits the force forward through the outer shell 1 and the second support ring 22, which can reduce the impact on aerodynamics. More specifically, the umbrella tube 3 is connected to the edge of the outlet with a corner piece 24 to further reduce the impact on aerodynamics. More specifically, the corner piece 24 is rounded.

[0037] like Figure 4 and Figure 5 As shown, the side of the shell 1 is provided with an exhaust port 4, and the exhaust port 4 is plugged with an exhaust pipe 5. In this embodiment, the side of the shell 1 refers to the position of the shell 1 in the relative space relative to the aircraft after the shell 1 is correctly installed on the tail of the aircraft. Specifically, the exhaust port 4 is arranged on one of the side panel walls 11 and is located between the first support ring 21 and the second support ring 22. The exhaust port 4 is arranged on the side to prevent the liquid discharged from the front of the aircraft from flowing along the bottom of the aircraft to the tail, and the liquid enters the shell 1 through the exhaust port 4. Since the temperature inside the shell 1 is high during the test flight, the sealing performance is poor, and if it is a flammable liquid, it is easy to cause danger. In addition, the exhaust port 4 is located on the side to prevent the gas discharged from the exhaust port 4 from going downward, and to prevent the maintenance personnel from being harmed by the hot air when passing under the aircraft, thereby improving the safety of the maintenance personnel. More specifically, in this embodiment, since the air flow velocity of the exhaust pipe 5 is small, the exhaust pipe 5 is a curved pipe that is conveniently installed in the exhaust port 4 on the side of the shell 1, which can further optimize the internal structure and improve the utilization rate of the space. Exemplarily, the exhaust pipe 5 can be formed by integral casting or by splicing two semicircular sheet metal parts. Further, the exhaust pipe 5 is passed through the second support ring 22. In order to alleviate the vibration caused by the impact of the airflow, at least one fixed support 6 is provided on the second support ring 22, and the exhaust pipe 5 is fixed on the fixed support 6.

[0038] Since the temperature inside the outer shell 1 is relatively high, the tail cone of the aircraft stall recovery parachute is also provided with a heat insulation structure, which includes a parachute tube heat insulation layer and a support heat insulation layer. The parachute tube heat insulation layer is arranged on the inner side of the parachute tube 3 to ensure that the stall recovery parachute body works normally and is not affected by high temperature; the support heat insulation layer is arranged on the side of the blocking portion 25 facing the inner side of the outer shell 1, thereby ensuring the structural stability of the blocking portion 25 and the first support ring 21. It can be understood that in other embodiments, the second support ring 22 and the support portion 23 can also be provided with a support heat insulation layer.

[0039] The tail cone of the aircraft stall recovery parachute is also provided with an inspection port 7, which is arranged opposite to the exhaust port 4 for easy maintenance. Specifically, the inspection port 7 is arranged on the side panel wall 11 opposite to the exhaust port 4. The size of the inspection port 7 is sufficient for the maintenance personnel to enter with their whole body or upper body. The inspection port 7 is located between the first support ring 21 and the second support ring 22, and the inspection port 7 is provided with an inspection cover 8 opened to the outside. The shape of the inspection cover 8 is not specifically limited, and can be square, round or oval, so long as it can block the inspection port 7.

[0040] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. The tail cone is modified with a parachute to recover from stall, characterized in that: include: Housing (1); A support ring assembly (2), the support ring assembly (2) comprising a first support ring (21) and a second support ring (22), the first support ring (21) and the second support ring (22) being supported in the housing (1) at intervals, the first support ring (21) being provided with a blocking portion (25) for blocking the rear end of the housing (1), the blocking portion (25) being provided with an outlet; An umbrella tube (3), the umbrella tube (3) being arranged obliquely in the shell (1), the umbrella tube (3) being passed through the first support ring (21) and the second support ring (22), a portion of the umbrella tube (3) passing through the outlet, and an angle piece (24) being connected between the umbrella tube (3) and the edge of the outlet.

2. The aircraft stall recovery parachute modified tail cone according to claim 1, characterized in that: The umbrella tube (3) is arranged obliquely from the bottom of the shell (1) to the top of the shell (1).

3. The aircraft stall recovery parachute modified tail cone according to claim 1, characterized in that: The second support ring (22) is provided with a support portion (23), the support portion (23) extending along the inner side of the second support ring (22) toward the central axis of the outer shell (1), the support portion (23) is provided with a through groove, and the umbrella tube (3) abuts against the through groove so as to be supported by the support portion (23).

4. The aircraft stall recovery parachute modified tail cone according to claim 1, characterized in that: An exhaust port (4) is provided on the side of the housing (1), and an exhaust pipe (5) is plugged into the exhaust port (4).

5. The aircraft stall recovery parachute modified tail cone according to claim 4, characterized in that: The exhaust pipe (5) is a bent pipe, and the exhaust pipe (5) is passed through the second support ring (22). The second support ring (22) is provided with at least one fixed support (6), and the exhaust pipe (5) is fixed on the fixed support (6).

6. The aircraft stall recovery parachute modified tail cone according to claim 4, characterized in that: A heat insulation structure is also provided, the heat insulation structure comprising an umbrella tube heat insulation layer, the umbrella tube heat insulation layer being arranged on the inner side of the umbrella tube (3).

7. The aircraft stall recovery parachute modified tail cone according to claim 6, characterized in that: The heat insulation structure further comprises a supporting heat insulation layer, wherein the supporting heat insulation layer is arranged on a side of the sealing portion (25) facing the inner side of the outer shell (1).

8. The aircraft stall recovery parachute modified tail cone according to claim 4, characterized in that: A maintenance opening (7) is provided on the side of the housing (1), and the maintenance opening (7) is arranged opposite to the exhaust port (4).

9. The aircraft stall recovery parachute modified tail cone according to claim 8, characterized in that: The inspection opening (7) is located between the first supporting ring (21) and the second supporting ring (22), and an inspection cover (8) opening outward is provided on the inspection opening (7).

10. The aircraft stall recovery parachute modified tail cone according to claim 1, characterized in that: The housing (1) comprises two side panel walls (11), the side parts of the two side panel walls (11) are connected to form a truncated cone shape, and a wall panel docking piece (12) is provided between the connecting parts of the side panel walls (11) so as to enable connection via the wall panel docking piece (12).

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