CN213735576U - Aircraft stall departure device mounting assembly - Google Patents

Abstract

The utility model relates to an aircraft stall improves device installation component, it includes: a housing; the umbrella barrel is fixed at the top of the shell, and a stall-changing out umbrella component is installed in the umbrella barrel; a plurality of stringers, each of the plurality of stringers configured to be connected at one end to the housing and at another end adapted to be connected to a fuselage of the aircraft, wherein the housing is provided with a top opening, and the bucket is disposed at the top opening of the housing in a half-buried manner such that a portion of a volume of the bucket is buried inside a cavity enclosed by the housing and another portion of the volume of the bucket is exposed outside the housing. Therefore, enough installation space is ensured, and overlarge aerodynamic influence on the airplane can be avoided.

Description

Aircraft stall departure device mounting assembly

Technical Field

The utility model relates to an aircraft tries to fly technical field, specifically relates to an aircraft stall that uses when aircraft stall performance tries to fly installs the subassembly.

Background

Stall refers to the situation that the attack angle of an airplane or a wing is larger than the maximum lift attack angle, so that the airplane cannot keep a normal flying state, longitudinal or transverse instability is generated in severe cases, and the airplane can be out of control. There is a clear specification in the relevant articles for stall, and civil transport aircraft must be tested for stall performance. The stall test flight of the airplane is a test flight subject with high difficulty and high risk, once the airplane enters deep stall, a pilot can hardly or even cannot carry out the stall test flight by using a common method for carrying out the stall test flight. In order to ensure the safety of the airplane and test pilots during stall test flight, a stall/tail spin transformation parachute is usually additionally arranged at the tail section of the airplane, a parachute arranged at the rear part of the airplane is thrown towards a specific direction by a rocket, and the stall attitude of the airplane is changed by the parachute for transforming a deep stall state.

The stall extraction device needs to be designed according to different situations of the test airplane type and the stall extraction parachute system. In the prior art, a stall extraction device is arranged on the outer side of some types of airplanes, so that the pneumatic influence on the airplanes is large, and the performance of the airplanes in test flight is influenced. In other aircraft models, the stall extraction device is arranged on the inner side of the tail section of the aircraft, which requires a large enough installation space for the tail section of the aircraft and limits the size of the umbrella.

SUMMERY OF THE UTILITY MODEL

The utility model aims at: the installation component of the airplane stall extraction device is high in space structure efficiency. The outer shell of the stall improvement device mounting assembly replaces and substantially conforms to the profile of the original tail section of the aircraft; the mounting assembly of the airplane stall transformation device balances airplane aerodynamic influence caused by appearance modification and insufficient mounting space of an airplane tail section by adopting a semi-buried mode; an umbrella barrel structure for stall transformation of the umbrella is additionally arranged at the top of the tail section of the airplane in a semi-buried mode, and a certain smooth transition area is formed between the umbrella barrel and the outer shell, so that the influence on the pneumatic performance of the airplane is small; the tail end frame is changed into a bearing joint for transferring the load of the stall-changed umbrella, and simultaneously the load is transferred to the front section of the airplane rear fuselage through a plurality of external stringers.

Therefore, the utility model provides an aircraft stall improves device installation component, it includes: a housing; an umbrella barrel fixed to the top of the housing, the barrel having a stall-modifying umbrella assembly mounted therein; the aircraft comprises a plurality of stringers, wherein one end of each stringer is connected with a shell, the other end of each stringer is suitable for being connected with an aircraft body, the shell is provided with a top opening, an umbrella barrel is arranged at the top opening of the shell in a semi-buried mode, a part of volume of the umbrella barrel is buried in a cavity formed by the shell in an enclosing mode, the other part of volume of the umbrella barrel is exposed out of the shell, and the umbrella barrel and the shell are riveted through a plurality of shearing angle pieces.

According to one aspect of the present invention, the housing is provided with a maintenance opening and an auxiliary power unit exhaust opening on a side opposite to the top opening, and the material of the housing is a titanium alloy with a thickness in the range of 0.8-3 mm.

According to an aspect of the present invention, the power cable further comprises a bearing joint fixed at the end of the housing, wherein the bearing joint is integrally formed as a unitary piece, and wherein the bearing joint is made of steel and has a thickness in the range of 50-100 mm.

According to the utility model discloses an aspect, the load connects the inboard and is provided with many ribs, and many ribs are fan-shaped distribution, and wherein, are provided with the bolt hole in the cross section of rib to connect the stiff end that the stall changed out the umbrella rope of umbrella.

According to one aspect of the present invention, the top of the force bearing joint includes a top notch and a portion of the umbrella barrel is placed in the top notch.

According to an aspect of the present invention, the shear horn has rounded corners to form a smooth transition.

According to an aspect of the present invention, the umbrella barrel is made of steel, the inner diameter is in the range of 250-350mm, and the length is in the range of 800-900 mm.

According to an aspect of the utility model, the umbrella bucket is the cylinder, inserts the inside of the cavity that the shell enclosure formed along 35% to 45% of the axial length of umbrella bucket to 55% to 65% of axial length extend backward outside the cavity that the shell enclosure formed, in order to form half the form of burying.

According to an aspect of the utility model, the umbrella bucket is the cylinder, and the bottom of umbrella bucket is equipped with outstanding strip portion to the partly placing in top notch department of strip portion plays right effect.

According to the utility model discloses an aspect, every in many stringers is formed by the concatenation of multistage longeron, and wherein, the one end of every in many stringers and the architrave fixed connection that the load connects to many stringers are connected through high lock bolt along the covering and the shell of length direction and the fuselage of aircraft.

Adopt the basis the utility model discloses an aircraft stall transformation device installation component makes partly inside the aircraft tail section of umbrella bucket, and another part is outside at the tail section, and this has guaranteed sufficient installation space to smooth transition between umbrella bucket and the tail section shell, thereby can not bring too big pneumatic influence for the aircraft.

Drawings

Fig. 1 is a perspective view of an aircraft stall extraction device mounting assembly in accordance with a preferred embodiment of the present invention;

FIG. 2 is a perspective view of the housing of the aircraft stall extraction device mounting assembly of the preferred embodiment;

FIG. 3A is a perspective view of the messenger joint of the aircraft stall extraction device mounting assembly of the preferred embodiment;

fig. 3B is an elevation view of the messenger joint of the aircraft stall extraction device mounting assembly according to a preferred embodiment of the present invention;

FIG. 4 is a perspective view of the umbrella barrel of the aircraft stall extraction device mounting assembly according to a preferred embodiment of the present invention; and

fig. 5 is a front view of a stringer of an aircraft stall extraction device mounting assembly according to a preferred embodiment of the present invention.

List of reference numerals

1 aircraft stall departure device mounting assembly

10 outer casing

11 open at the top

12 maintenance port

13 auxiliary power unit exhaust port

14 shear angle piece

20 bearing joint

21 top notch

22 rib

23 bolt hole

30 umbrella barrel

31 strip-shaped part

40 stringer

Detailed Description

In the present invention, the definition "front" is the direction (i.e. the course towards the aircraft) away from the tail section of the aircraft, and the definition "top" is the direction away from gravity.

In the present application, the terms "substantially", "about" are approximately plus or minus 5% to describe a particular numerical value such as length, angle, etc.

The present invention will be further described with reference to the following embodiments and drawings, and more details will be set forth in the following description in order to provide a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions according to the actual application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the embodiments.

Fig. 1 shows a stall extraction device mounting assembly 1 according to a preferred embodiment of the present invention. The utility model discloses an in the preferred embodiment, stall improves device installation component 1 and uses in the stall test flight test of large aircraft as the repacking replacement structure of stall improvement umbrella system, changes out the device with stall and installs the aircraft afterbody, changes out the umbrella system for stall and provides installation space, can spread the load transmission of umbrella to the load structure of fuselage behind the aircraft simultaneously, and it is less to the aerodynamic performance influence of aircraft after the repacking.

Stall extraction device mounting assembly 1 comprises a housing 10, an outrigger joint 20, a parachute bucket 30 for storing a collapsed stall extracted parachute (not shown), and a plurality of stringers 40 for transferring the load of the parachute to the fuselage of the aircraft. When the airplane enters deep stall during test flight and cannot be taken out, the stall-taken out parachute is taken out from the parachute barrel 30 by the rocket and is opened in the air. The drag of the umbrella is transmitted by the parachute lines to the messenger sub 20 at the tail end of the aircraft and then to the messenger structure (not shown) at the forward section of the rear fuselage of the aircraft via the stringers 40. Thus imparting a nose down moment to the aircraft, thereby causing the aircraft to shift out of a stall condition.

Fig. 2 shows the housing 10 of the preferred embodiment. The outer casing 10 has a generally frusto-conical shape conforming to the shape of the original tail section of the test-flight aircraft. In the preferred embodiment, the housing 10 is constructed of a titanium alloy and has a thickness in the range of 0.8-3mm, preferably 1.8-2 mm. It will be appreciated that the material and thickness of the housing 10 is not limited thereto, and other strong and high temperature resistant materials may be used and the corresponding thickness dimensions selected according to the experimental requirements. As shown in fig. 2, the housing 10 has a top opening 11 at the top toward the rear end, and the top opening 11 is shaped to allow the umbrella barrel 30 to be fixed at an angle to the top of the housing 10 in a half-buried manner, which will be described in detail below.

As shown in fig. 1, the casing 10 is provided at a lower side with a maintenance port 12 and an Auxiliary Power Unit (APU) exhaust port 13, the maintenance port 12 making installation and maintenance inspection accessible, and the auxiliary power unit exhaust port 13 communicating with the auxiliary power unit is arranged to be opened downward so as not to be damaged by direct discharge of high-temperature gas to the parachute line of the stalled modified umbrella.

Fig. 3A and 3B show the carrier joint 20 of the preferred embodiment of the present invention. The carrier sub 20 is used to carry the load of the stall converted umbrella. The messenger joint 20 is integrally formed as a unitary piece for greater rigidity and stability. The messenger joint 20 is generally in the shape of a circular cap to be attached to the end of the housing 10, preferably riveted. The material of the force bearing joint 20 is steel, and the thickness is in the range of 50-100mm, and preferably in the range of 70-75 mm. It will be appreciated that the material and thickness of the messenger 20 is not limited thereto and that a suitably strong material and corresponding thickness dimensions may be selected as desired.

In the preferred embodiment, as shown in fig. 3B, 6 ribs 22 are provided inboard of the messenger 20, and preferably the ribs 22 are scalloped to receive and transmit the load from a stall converted umbrella more evenly. It will be appreciated that the number and distribution of the ribs 22 is not limited thereto, and that a suitable number and selection of a suitable distribution pattern, such as a well, triangle, etc., may be used as desired. The cross position of the rib of the tail end bearing joint is provided with 4 bolt holes for connecting the fixed end of the umbrella rope of the stall transformed umbrella. It will be appreciated that the number of bolt holes may vary depending on the number of umbrella cords. In addition, the messenger tab 20 according to the preferred embodiment includes a top notch 21 at the top, the top notch 21 aligning with the top opening 11 of the housing 10 for a portion of the umbrella barrel 30 to be placed therein when the messenger tab 20 is mated to the end of the housing 10, as will be described in detail below.

Figure 4 shows the umbrella barrel 30 of the preferred embodiment of the present invention. The parachute barrel 30 is used for storing the contracted stall converted parachute, and when the parachute is required to be thrown, a small rocket for taking the stall converted parachute out together can be launched from the parachute barrel. The parachute barrel 30 is substantially cylindrical and has an insulating layer attached inside. In a preferred embodiment, the umbrella barrel 30 is made of steel, the inner diameter is within the range of 250-; it will be appreciated that the material and dimensions of the umbrella barrel 30 are not so limited, and that suitable high strength materials and corresponding dimensions may be used as desired (depending on the size of the stall converted umbrella).

As shown in fig. 1, the umbrella barrel 30 is fixed at the top opening 11 of the aircraft tail section shell 10 in a half-buried manner, which means that in a preferred embodiment, a part of the volume of the umbrella barrel 30 is buried inside the cavity enclosed by the shell 10, and the other part of the volume is exposed outside the shell 10. In the preferred embodiment, the umbrella barrel 30 is generally cylindrical, inserted inside the casing 10 along approximately 35% to 45% of its axial length, and extending rearwardly beyond the cavity enclosed by the casing 10 for approximately 55% to 65% of its length. The semi-buried form can balance aerodynamic influence of the airplane caused by appearance change and insufficient installation space of the tail section of the airplane, and the aerodynamic influence is reduced as far as possible while enough installation space of the stall-improving umbrella system is obtained.

As shown in fig. 2, the umbrella barrel 30 is secured to the housing 10 by a ring of shear tabs 14, preferably riveted by the shear tabs 14. As shown in fig. 2, these shear horns 14 are generally elongated L-shaped horns with rounded corners that can be positioned as desired to provide a smooth transition between the umbrella barrel 30 and the outer casing 10 so as not to unduly aerodynamically affect the aircraft. Further, as shown in fig. 4, the umbrella barrel 30 has a protruding strip 31 at the bottom, and the strip 31 is used to store the rope of the closed stall converted umbrella. The width of the strip 31 is preferably in the range of 50-60mm and the protrusion height is preferably in the range of 30-35 mm. When the aircraft stall extraction device mounting assembly 1 of the present invention is in use, a portion of the strip 31 of the umbrella barrel 30 is placed over the top notch 21 of the carrier tab 20, as shown in fig. 1, but without a direct connection therebetween.

Fig. 5 shows a stringer 40 of a preferred embodiment of the invention. In the preferred embodiment, the stall modifying device mounting assembly 1 has a total of 4 external stringers. In the present embodiment, each stringer 40 is configured to be spliced from 5 sections of spar, preferably with stringers 40 being integrally formed. The material of stringer 40 is preferably a titanium alloy. The length of the stringer 40 is selected to be suitable for a heavy structure with one end connected to the heavy fitting 20 and the other end extending to the fuselage, preferably a heavy structure of the forward section of the rear fuselage of the aircraft, and the width is selected to be suitable for connection with a heavy structure of the forward section of the rear fuselage of the aircraft. One end of each stringer 40 is riveted with the frame edge of the force-bearing joint 20, and the other end extends to the outside of the force-bearing structure of the front section of the rear fuselage of the airplane and is riveted by penetrating through the skin of the fuselage, and wherein the stringers are external, and each section of the stringer is connected with the skin of the rear fuselage of the airplane and the shell 10 through high-lock bolts, so that the stringers 40 can transmit the load of the force-bearing joint 20 to the force-bearing structure of the front section of the rear fuselage.

Adopt according to the utility model discloses an aircraft stall transformation device installation component makes partly inside the aircraft tail section of umbrella bucket, and another part is outside at the tail section, and this has guaranteed sufficient installation space, can avoid again to bring too big pneumatic influence for the aircraft.

During the application of the installation component of the airplane stall extraction device, when the stall extraction umbrella is opened, the installation component can transmit the load of the umbrella to the airplane bearing structure through the bearing joint without damaging the tail section of the airplane, and the airplane obtains low head moment, so that the airplane is extracted from a stall state.

While various embodiments have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to those skilled in the relevant art that the disclosed subject matter can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, and not as a basis for any limitation on the invention.

Claims (10)

1. An aircraft stall extraction device mounting assembly (1), the aircraft stall extraction device mounting assembly (1) comprising:

a housing (10);

the umbrella barrel (30), the umbrella barrel (30) is fixed on the top of the shell (10), and a stall-improving umbrella component is installed in the umbrella barrel (30);

a plurality of stringers (40), each of said plurality of stringers (40) having one end connected to said outer shell (10) and another end adapted to be connected to a fuselage of an aircraft,

it is characterized in that the preparation method is characterized in that,

the outer shell (10) is provided with a top opening (11), the umbrella barrel (30) is arranged at the top opening (11) of the outer shell (10) in a semi-buried mode, so that one part of the volume of the umbrella barrel (30) is buried inside a cavity formed by the enclosure of the outer shell (10), and the other part of the volume of the umbrella barrel (30) is exposed out of the outer shell (10), and

the umbrella barrel (30) and the shell (10) are riveted by a plurality of shearing angle pieces (14).

2. The aircraft stall extraction device mounting assembly (1) of claim 1,

the shell (10) is provided with a maintenance port (12) and an auxiliary power device exhaust port (13) on the side opposite to the top opening (11), and the shell (10) is made of titanium alloy and has a thickness in the range of 0.8-3 mm.

3. The aircraft stall extraction device mounting assembly (1) of claim 1,

further comprising an messenger (20), the messenger (20) being fixed at the end of the outer shell (10), wherein the messenger (20) is integrally formed as a unitary piece, and wherein the material of the messenger (20) is steel and has a thickness in the range of 50-100 mm.

4. The aircraft stall extraction device mounting assembly (1) of claim 3,

the inner side of the bearing joint (20) is provided with a plurality of ribs (22), the plurality of ribs (22) are distributed in a fan shape, and bolt holes (23) are formed in the intersection of the ribs (22).

5. The aircraft stall extraction device mounting assembly (1) of claim 3,

the top of the messenger (20) includes a top notch (21) and a portion of the umbrella bucket (30) is placed at the top notch (21).

6. The aircraft stall extraction device mounting assembly (1) of claim 1,

the shear horn (14) has rounded corners.

7. The aircraft stall extraction device mounting assembly (1) of claim 1,

the umbrella barrel (30) is made of steel, the inner diameter is within the range of 250-350mm, and the length is within the range of 800-900 mm.

8. The aircraft stall extraction device mounting assembly (1) of claim 1,

the umbrella barrel (30) is cylindrical, is inserted into the cavity enclosed by the outer shell (10) along 35 to 45 percent of the axial length of the umbrella barrel (30), and extends backwards outside the cavity enclosed by the outer shell (10) along 55 to 65 percent of the axial length.

9. An aircraft stall extraction device mounting assembly (1) as claimed in claim 5, wherein the bucket (30) is cylindrical, the bottom of the bucket (30) is provided with a protruding strip (31), and a portion of the strip (31) is placed at the top recess (21).

10. The aircraft stall extraction device mounting assembly (1) of claim 3,

each of the plurality of stringers (40) is formed by splicing a plurality of sections of stringers, wherein one end of each of the plurality of stringers (40) is fixedly connected with a rim of the force-bearing joint (20), and the plurality of stringers (40) are connected with a skin of a fuselage of an aircraft and the shell (10) through high-lock bolts in a length direction.

Images