CN216332809U - Helicopter tail servo fairing capable of resisting bird collision - Google Patents
Helicopter tail servo fairing capable of resisting bird collision Download PDFInfo
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- CN216332809U CN216332809U CN202122678107.XU CN202122678107U CN216332809U CN 216332809 U CN216332809 U CN 216332809U CN 202122678107 U CN202122678107 U CN 202122678107U CN 216332809 U CN216332809 U CN 216332809U
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- fairing
- leading edge
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- cone
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Abstract
The utility model provides a helicopter tail servo fairing for resisting bird strike, which comprises: the servo fairing comprises a front edge servo fairing (1), a rear edge servo fairing (2), an upper bracket (3) and a lower bracket (4); the front edge servo fairing (1) is connected with the rear edge servo fairing (2) to form a combined airfoil, and the upper bracket (3) is connected with the lower bracket (4) and arranged on the inner side of the combined airfoil and supports the combined airfoil; the leading edge servo fairing (1) comprises: a leading edge skin (5) and a leading edge cone (6); the leading edge cone (6) is fixedly arranged on the outer side of the leading edge skin (5), a cavity with a triangular section is formed between the leading edge cone (6) and the leading edge skin (5), the cone edge of the leading edge cone (6) is used for cutting an impacted bird body, and the cavity is used for absorbing and dissipating impact energy of the bird body.
Description
Technical Field
The utility model belongs to the technical field of helicopters, and particularly relates to a helicopter tail servo fairing capable of resisting bird collision.
Background
The civil helicopter mainly executes flight tasks such as public security patrol, forest fire prevention, aerial photography, emergency rescue, cargo transportation, marine operation and the like. Because the civil helicopters are frequently in a low-altitude flight state when performing tasks, the probability that the civil helicopters are collided with birds is high, and the bird collision event becomes a main event threatening the flight safety of the civil helicopters.
CCAR-29 Properly rules for Transporter rotorcraft 631 article of bird strikes: rotorcraft must be designed to speed up to 2440 meters (8000 feet) at a speed equal to VNEOr VH(smaller) continued safe flight and landing (for class A) or safe landing (for class B) after a bird strike of 1.0 kg (2.2 pounds), compliance must be demonstrated by trial or analysis based on trial on a similar design structure with sufficient representativeness (where: VNEAn insurmountable speed; vHMaximum fly-by speed). Existing helicopters typically employ additional structures such as spars within the leading edge of the wing to provide strength.
However, for a helicopter with a high tail rotor, a tail reducer, a tail servo actuator and related hydraulic pipelines are positioned in an exposed area at the top of a vertical tail and are positioned at a key part of a bird collision area, once the helicopter is impacted by a bird in the flying process, the tail servo actuator is damaged, and more serious catastrophic results can be caused. Compared with the common wing part, the tail servo fairing is small in space and more in equipment, and the problem that the bird impact resistance is poor due to the fact that the number of beams is increased simply is solved.
SUMMERY OF THE UTILITY MODEL
The utility model provides a helicopter tail servo fairing capable of resisting bird collision, which can be quickly disassembled and assembled, has a simple process and can improve bird collision resistance.
The utility model provides a helicopter tail servo fairing for resisting bird strike, which comprises: a leading edge servo fairing 1, a trailing edge servo fairing 2, an upper bracket 3 and a lower bracket 4; wherein the content of the first and second substances,
the leading edge servo fairing 1 and the trailing edge servo fairing 2 are connected to form a combined airfoil, and the upper bracket 3 and the lower bracket 4 are connected and arranged on the inner side of the combined airfoil and support the combined airfoil;
the leading edge servo cowl 1 comprises: a leading edge skin 5 and a leading edge cone 6;
the leading edge cone 6 is fixedly arranged on the outer side of the leading edge skin 5, a cavity with a triangular section is formed between the leading edge cone 6 and the leading edge skin 5, the cone edge of the leading edge cone 6 is used for cutting an impacted bird body, and the cavity is used for absorbing and dissipating impact energy of the bird body.
Optionally, the leading edge cone 6 is formed by adding.
Optionally, the leading edge servo fairing 1 further comprises: a leading edge first rib 7, a leading edge second rib 8;
the leading edge first rib 7 and the leading edge second rib 8 are placed perpendicular to the leading edge skin 5 airfoil and are riveted with the leading edge skin 5.
Optionally, the leading edge servo fairing 1 further comprises: a leading edge tail section 9;
the leading edge tail section 9 is connected with the leading edge skin 5 through rivets, and the leading edge tail section 9, the upper support 3 and the lower support 4 are respectively positioned at two ends of the leading edge servo fairing 1 so as to improve the strength of the end parts.
Optionally, the trailing edge servo cowl 2 is connected to the leading edge servo cowl 1 by a quick release lock.
Optionally, the profile of the leading edge servo fairing is designed to be at a 20 ° sweep angle.
The utility model provides a helicopter tail servo fairing capable of resisting bird collision, which can fully absorb or dissipate impact energy of a bird body by increasing the energy absorption characteristic and the dissipation characteristic of a structure, and proved by bird collision test, the bird collision area has no obvious deformation and an internal tail servo actuating mechanism runs normally. The bird strike prevention purpose can be achieved, and the effect of protecting the servo mechanism of the tail reducer is achieved; the device has the advantages of quick disassembly and assembly and convenient maintenance of internal mechanisms; meanwhile, the used parts have no special process, and the production and manufacturing process is simple.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of a helicopter tail servo fairing for resisting bird strike according to the present invention;
FIG. 2 is a schematic view of a leading edge servo fairing provided in accordance with the present invention with the skin hidden;
FIG. 3 is a schematic view of a leading edge cone provided by the present invention;
FIG. 4 is a schematic view of a leading edge cone attachment provided by the present invention;
FIG. 5 is a schematic view of the sweep angle of the leading edge servo fairing provided by the present invention;
description of reference numerals:
1-leading edge servo cowling; 2-trailing edge servo cowling;
3-mounting a bracket; 4-lower support;
5-leading edge skin; 6-leading edge cone;
7-leading edge first rib; 8-a leading edge second rib;
9-leading edge tail section; 10-a torsion box;
11-corner boxes; 12-an upper connection;
13-lower connector; 14-a corner box;
15-angle piece.
Detailed Description
The following explains the bird strike resistant helicopter tail servo fairing provided by the utility model with reference to the accompanying drawings.
Referring to fig. 1-5, the present invention provides a helicopter tail servo fairing that resists bird strikes.
In the utility model, the bird impact resistance function is mainly realized by the front edge servo fairing, so that the bird impact resistance of the front edge tail servo fairing is improved by mainly increasing the energy absorption characteristic and the energy dissipation characteristic of the structure during design, so that the bird impact resistance function can fully absorb or dissipate the impact energy of a bird body. When the leading edge and tail servo fairing encounters bird strike, the impact force can form an instantaneous bending effect on the structure, and the leading edge part and the connecting part of the leading edge and tail servo fairing need to play a role in balancing bending moment, so that the phenomenon that the leading edge and tail servo fairing deforms too much to damage an internal servo actuator is avoided.
Fig. 1 is a schematic view of a tail servo fairing, and as shown in fig. 1, the bird strike resistant helicopter tail servo fairing provided by the utility model comprises: a leading edge servo fairing 1, a trailing edge servo fairing 2, an upper bracket 3 and a lower bracket 4; wherein the content of the first and second substances,
the servo fairing 2 at the rear edge is connected with the servo fairing 1 at the front edge through a quick-release lock, so that the servo fairing 2 at the rear edge can be quickly detached, and the maintenance of a servo mechanism is facilitated. Both of which make up the composite airfoil. The leading edge servo fairing 1 is connected with an upper bracket 3 and a lower bracket 4 through screws. Wherein the function of resisting bird strikes is mainly realized by the leading edge servo fairing 1.
FIG. 2 is a schematic view of a leading edge servo fairing with its skin hidden, FIG. 3 is a schematic view of a forward cone, and FIG. 4 is a schematic view of a leading edge cone attachment.
As shown in fig. 2, the leading edge servo cowl 1 includes: the front edge comprises a front edge skin 5, a front edge cone 6, a front edge first rib 7, a front edge second rib 8, a front edge tail section 9, a torsion box 10, a corner box 11, an upper connecting piece 12 and a lower connecting piece 13; wherein the content of the first and second substances,
as shown in fig. 3 and 4, the leading cone 6 is connected to the leading skin 5 using two rows of rivets. The leading edge cone 6 is used for increasing the bending resistance of the leading edge, simultaneously, the bird body is cut by the cone structure after being impacted, the energy of the bird body is divided, the structure is protected from being broken down, and the impact energy of the bird body can be absorbed and dissipated by the cavity structure between the leading edge cone 6 and the leading edge skin 5.
Optionally, the nose cone 6 is integrally formed.
As shown in FIG. 2, the leading edge first rib 7 and the leading edge second rib 8 are placed perpendicular to the airfoil shape of the leading edge skin 5 and are riveted with the leading edge skin 5 for improving local strength and rigidity, and cavities between the ribs can consume the impact energy of the bird body.
Further, the leading edge tail section 9 is connected with the leading edge skin 5 through rivets, the leading edge tail section 9, the upper support 3 and the lower support 4 are respectively located at two ends of the leading edge servo fairing 1, and the strength of the end part can be improved through a closed box section, so that the bird body impact energy dissipated by the leading edge can be borne, and the structural integrity of the wing profile is further guaranteed.
Further, the torque box 10 is rivet-connected to the leading edge skin 5, rivet-connected to the supported leading edge first rib 7 and the leading edge second rib 8, and an opening portion of the torque box 10 is reinforced with a corner box 11. The torque box 10, while supporting the ribs, primarily prevents the energy impacting the skin surface after a bird strike from causing the structure to twist.
Furthermore, the upper bracket 3 and the lower bracket 4 are provided with corner pieces 15 through riveting, and the corner pieces 15 are provided with quick-release lock seats for connecting with the tail speed reducer fairing.
And the upper connecting piece 12 and the lower connecting piece 13 are provided with quick-release lock seats for mounting the trailing edge servo fairing 2, and the upper connecting piece 12 and the lower connecting piece 13 are connected with the leading edge skin 5 through rivets and are respectively connected with the upper bracket 3 and the lower bracket 4 through 1 screw. The angle box 14 is riveted with the front edge tail section 9, the front edge skin 5, the upper connecting piece 12 and the lower connecting piece 13, and the closed cavity formed by the angle box 14 and the front edge tail section 9 strengthens the rigidity of the whole servo fairing.
Fig. 5 is a schematic diagram of the leading edge sweepback angle, and as shown in fig. 5, the profile of the leading edge servo fairing is designed to be 20 degrees of sweepback angle, so that after the bird body is impacted at high speed, the bird body can conveniently flow out from the end face of the leading edge servo fairing, and the aims of changing the change trend of bird impact energy and increasing the bird impact resistance of the structure are fulfilled.
The technical scheme adopted by the utility model is as follows:
1. the front edge cone is riveted at the direct impact part, the conical part can effectively increase the bending resistance of the front edge, and the installation of the front edge cone enables the bird body to be cut by the cone structure after being impacted, so that the energy of the bird body is divided, and the structure is protected from being broken down. Meanwhile, the cavity structure formed between the leading edge cone and the leading edge skin can absorb and dissipate the impact energy of the bird body.
2. The internal and external spaces and aerodynamic shapes are comprehensively considered, and the 20-degree front edge servo fairing sweep angle is designed, and researches show that under high-speed impact, the bird body shows obvious hydrodynamic behavior, so that the appropriate sweep angle of the front edge structure is convenient for the bird body to flow out from the end face of the front edge servo fairing after impact, and the aims of changing the change trend of bird impact energy and increasing the bird impact resistance of the structure are fulfilled.
3. The closed box sections are respectively added at the two ends of the fairing to improve the strength and rigidity of the end parts so as to bear the impact energy of the bird body after being dissipated by the front edge, thereby ensuring the structural integrity of the airfoil profile;
4. the front edge rib is arranged to improve the local strength and rigidity, and the cavity between the rib and the end face can consume the impact energy of the bird body;
5. the torsion box is installed to support the ribs while preventing the energy from impacting the skin surface after a bird strike from causing torsion of the structure.
Claims (6)
1. A helicopter tail servo fairing that resists bird strikes, comprising: the servo fairing comprises a front edge servo fairing (1), a rear edge servo fairing (2), an upper bracket (3) and a lower bracket (4); wherein the content of the first and second substances,
the leading edge servo fairing (1) and the trailing edge servo fairing (2) are connected to form a combined airfoil, and the upper bracket (3) is connected with the lower bracket (4) and arranged on the inner side of the combined airfoil and supports the combined airfoil;
the leading edge servo fairing (1) comprises: a leading edge skin (5) and a leading edge cone (6);
the front edge cone (6) is fixedly arranged on the outer side of the front edge skin (5), a cavity with a triangular section is formed between the front edge cone (6) and the front edge skin (5), the cone edge of the front edge cone (6) is used for cutting an impacted bird body, and the cavity is used for absorbing and dissipating impact energy of the bird body.
2. The fairing as claimed in claim 1, characterized in that said leading-edge cone (6) is integrally formed.
3. The fairing according to claim 1, characterized in that said leading edge servo fairing (1) further comprises: a leading edge first rib (7) and a leading edge second rib (8);
the leading edge first rib (7) and the leading edge second rib (8) are perpendicular to the wing shape of the leading edge skin (5) and are connected with the leading edge skin (5) in a riveting mode.
4. The fairing according to claim 3, characterized in that said leading edge servo fairing (1) further comprises: a leading edge tail section (9);
the front edge tail section (9) is connected with the front edge skin (5) through rivets, and the front edge tail section (9), the upper support (3) and the lower support (4) are respectively located at two ends of the front edge servo fairing (1) so as to improve the strength of the end parts.
5. The fairing according to claim 1, characterized in that the trailing edge servo fairing (2) is connected to the leading edge servo fairing (1) by means of a quick release lock.
6. The fairing as recited in claim 1, wherein said leading edge servo fairing profile is designed for a 20 ° sweep.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122678107.XU CN216332809U (en) | 2021-11-03 | 2021-11-03 | Helicopter tail servo fairing capable of resisting bird collision |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122678107.XU CN216332809U (en) | 2021-11-03 | 2021-11-03 | Helicopter tail servo fairing capable of resisting bird collision |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216332809U true CN216332809U (en) | 2022-04-19 |
Family
ID=81135153
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122678107.XU Active CN216332809U (en) | 2021-11-03 | 2021-11-03 | Helicopter tail servo fairing capable of resisting bird collision |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216332809U (en) |
-
2021
- 2021-11-03 CN CN202122678107.XU patent/CN216332809U/en active Active
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