A whole machine ballistic parachute rescue system of a light amphibious sports aircraft

Abstract

The application discloses a whole machine ballistic parachute landing lifesaving system of a light amphibious sports aircraft, which comprises a sandwich type machine body main frame and a longitudinal bearing machine body frame, detachable left wings and right wings are arranged in the machine body main frame in a staggered mode, the extension sections of the left main wing beam of the left wing and the right main wing beam of the right wing are connected with the machine body main frame through high-strength pins, and the high-strength pins serve as front suspension points of a parachute pack; the longitudinal bearing machine body frame is arranged at the rear of the machine body main frame along the axial direction of the sports aircraft, and rear suspension points of the parachute pack are arranged on the longitudinal bearing machine body frame; through the design, the local structure high bearing characteristics are effectively utilized, the parachute pack is hung, and the large overload coefficient load caused when the parachute pack is punched out and unfolded is borne; through the arrangement of the two front suspension points and the rear suspension point, a stable posture of the whole machine hanging is formed, and the aircraft has the emergency parachute landing capacity.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of general aviation light amphibious sports aircraft, and particularly relates to a whole machine ballistic parachute rescue system of a light amphibious sports aircraft. BACKGROUND

[0002] In the field of general aviation aircraft, the existing parachute rescue system is mostly configured for aircraft taking off and landing on land, but for amphibious light sports aircraft with detachable left and right wings and high-mounted engines, due to the significant difference in body layout and structural characteristics, there is a lack of an effective whole machine parachute rescue system that meets the requirements of airworthiness regulations.

[0003] When driving a light sports aircraft, the aircraft may encounter emergency situations such as engine failure, and the parachute rescue system can play a crucial role in such critical situations to save the lives of pilots and passengers. For amphibious light sports aircraft with detachable wings and high-mounted engines, a parachute rescue system must be specially developed according to the structure, installation, and propulsion system configuration characteristics to enable the aircraft to have emergency parachute landing capability. SUMMARY

[0004] The purpose of the present application is to provide a whole machine ballistic parachute rescue system of a light amphibious sports aircraft, which can have a parachute rescue system when the light amphibious sports aircraft encounters an emergency situation, save the lives of pilots and passengers, reduce aircraft damage, and reduce losses.

[0005] The technical scheme of the present application is a whole machine ballistic parachute rescue system of a light amphibious sports aircraft, which comprises a sandwich type main frame and a longitudinal load-bearing frame, characterized in that: detachable left and right wings are arranged in the main frame; high-strength pins are arranged through the main frame, the left wing, and the right wing; and the high-strength pins are the front suspension points of the parachute.

[0006] The longitudinal load-bearing frame is arranged behind the main frame along the axis of the sports aircraft, and the rear suspension points of the parachute are arranged on the longitudinal load-bearing frame.

[0007] The parachute is connected to the front suspension points and the rear suspension points through main cables, and is arranged in a parachute bag, which is arranged between the main frame and the longitudinal load-bearing frame.

[0008] A rocket mounting seat is arranged on any side of the parachute bag, and a ballistic rocket is arranged on the rocket mounting seat, the ballistic rocket is connected to the parachute in the parachute bag, and the ballistic rocket is launched to take out the parachute in the parachute bag.

[0009] As preferred, the fuselage main frame comprises a fuselage front main frame and a fuselage rear main frame arranged in front and behind, and the left wing and the right wing are staggered between the fuselage front main frame and the fuselage rear main frame.

[0010] As preferred, the right main spar of the right wing extends from the wing root to the left wing direction until it extends between the wing root of the left wing and the fuselage front main frame or the fuselage rear main frame, and the high-strength pin is sequentially penetrated through the fuselage front main frame, the right main spar, the left wing, and the fuselage rear main frame or the fuselage front main frame, the left wing, the right main spar, and the fuselage rear main frame.

[0011] As preferred, the right main spar of the right wing extends from the wing root to the left wing direction until it extends between the wing root of the left wing and the fuselage front main frame or the fuselage rear main frame, and the high-strength pin is sequentially penetrated through the fuselage front main frame, the right main spar, the left wing, and the fuselage rear main frame or the fuselage front main frame, the left wing, the right main spar, and the fuselage rear main frame.

[0012] As preferred, a support structure for carrying the parachute bag is arranged between the fuselage main frame and the longitudinal load-bearing fuselage frame, and the support structure is arranged on the fuselage between the fuselage main frame and the longitudinal load-bearing fuselage frame, and the support structure comprises a bracket one and a bracket two, which carry the parachute bag and make the parachute bag form an angle with the front propeller on the top of the fuselage.

[0013] As preferred, an opening is arranged on the skin of the fuselage corresponding to the top of the support structure, and a decorative cover plate is arranged on the opening.

[0014] As preferred, the rocket mounting seat is independently arranged in the support structure on any side of the parachute bag, the launch trajectory of the ballistic rocket is towards the top of the support structure, and the launch trajectory forms an angle with the vertical plane where the front propeller on the top of the fuselage is located, so that the parachute carried by the ballistic rocket avoids the front propeller.

[0015] As preferred, the tail of the ballistic rocket is connected with a trigger cable, and the trigger cable is connected with a trigger handle, which extends into the cockpit so that the pilot can directly operate.

[0016] As preferred, a U-shaped connecting piece is fixedly arranged on the rear hanging point, and the main cable is fixedly connected with the rear hanging point through the U-shaped connecting piece.

[0017] As preferred, the length of the main cable is configured according to the attitude of the fuselage, and the main cable is stored on the fuselage when it is not stretched out, and the surface is covered with a decorative material, which is different from the skin of the fuselage so that the operator can accurately find the arrangement path of the main cable.

[0018] Beneficial effects:

[0019] (1) The application utilizes the high load-bearing characteristics of the specially designed extension section of the wing and the main load-bearing point of the fuselage to eliminate the load caused by the large overload coefficient when the parachute is triggered and opened;

[0020] (2) The application adjusts the body attitude when the parachute is stable by adjusting the length ratio of the front and rear cables through a three-point cable layout;

[0021] (3) In the application, the main cable is embedded in the surface of the fuselage skin, the path is clear and direct, which is conducive to the smooth extraction of the main cable and can remind the aircraft user and operator not to block the path;

[0022] (4) The application adjusts the launch trajectory of the ballistic rocket and the parachute to avoid the working range of the propeller, significantly reducing the possibility of damage caused by the propeller hitting the parachute after it is extracted from the fuselage. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a structural schematic diagram of the application without the fuselage and wing skin;

[0024] Figure 2 is Figure 1 a partial detail view A in

[0025] Figure 3 is a structural schematic diagram of the application with the fuselage and wing skin;

[0026] Figure 4 is a side rear view of the application without the fuselage skin;

[0027] Figure 5 is a side front view of the application without the fuselage skin;

[0028] Figure 6 is Figure 5 a partial detail view B in

[0029] Figure 7 is Figure 5 a partial detail view C in

[0030] Figure 8 is a partial exploded view of the installation of the two front main cables of the parachute in the application;

[0031] Figure 9 is an overview of the installation of the parachute bag and the ballistic rocket in the application;

[0032] Figure 10 is Figure 9 a partial detail view D in

[0033] Figure 11 is a lateral schematic diagram of the application when triggered and expanded to a stable state.

[0034] The components include: 1. Main fuselage frame; 2. Longitudinal load-bearing fuselage frame; 3. Left wing; 4. Right wing; 5. High-strength pins; 6. Parachute pack; 7. Main cable; 8. U-shaped connector; 9. Support structure; 10. Front propeller; 11. Cover plate; 12. Rocket mount; 13. Ballistic rocket; 14. Decorative materials; 101. Forward main fuselage frame; 102. Rear main fuselage frame; 901. Support bracket one; 902. Support bracket two; 131. Trigger cable; 132. Trigger handle; 301. Left main wing spars; 401. Right main wing spars. Detailed Implementation

[0035] The present application will be further described below with reference to specific embodiments.

[0036] like Figures 1-9 The diagram shown is a structural schematic of the entire application and its various parts. In this embodiment, the application includes a sandwich-type fuselage main frame 1 and a longitudinally supporting fuselage frame 2. The fuselage main frame 1 includes a front fuselage main frame 101 and a rear fuselage main frame 102 arranged front to back. A detachable left wing 3 and a right wing 4 are alternately arranged in the front fuselage main frame 101 and the rear fuselage main frame 102.

[0037] In this embodiment, the left main wing spars 301 of the left wing 3 extends from the wing root toward the right wing 4 until it enters between the wing root of the right wing 4 and the forward main frame 101 of the fuselage. The high-strength bolts 5 located on the right side of the fuselage main frame 1 pass through the forward main frame 101, the left main wing spars 301, the right wing 4, and the rear main frame 102 of the fuselage in sequence. The right main wing spars 401 of the right wing 4 extends from the wing root toward the left wing 3 until it enters between the wing root of the left wing 3 and the rear main frame 102 of the fuselage. The high-strength bolts 5 located on the left side of the fuselage main frame 1 pass through the forward main frame 101, the left wing 3, the right main wing spars 401, and the rear main frame 102 of the fuselage in sequence.

[0038] In this embodiment, the high-strength pins 5 located on the left and right sides of the main frame 1 of the fuselage serve as the front suspension points of the parachute and are connected to the parachute via the main cable 7. The local bearing capacity at the high-strength pins 5 can reach 50kN, which is greater than the force required for the parachute to be deployed.

[0039] In this embodiment, the longitudinal support frame 2 is arranged behind the main frame 1 of the fuselage along the axial direction of the moving aircraft. A rear suspension point for the parachute is provided on the longitudinal support frame 2. A U-shaped connector 8 is fixedly provided on the rear suspension point. The main cable 7 is fixedly connected to the rear suspension point through the U-shaped connector 8.

[0040] In this embodiment, the parachute is arranged in the parachute bag 6, the parachute bag 6 is arranged in the support structure 9 between the fuselage main frame 1 and the longitudinal load-bearing fuselage frame 2, the support structure 9 comprises the bracket one 901 and the bracket two 902, the bracket one 901 and the bracket two 902 bear the parachute bag 6 and make the parachute bag 6 form an angle of 23° with the front propeller 10 on the top of the fuselage, when the parachute is opened after being launched by the ballistic rocket 13, the main cable 7 connected with the parachute can effectively avoid the front propeller 10.

[0041] In this embodiment, the skin on the fuselage corresponding to the top of the support structure 9 is provided with an opening, the opening is covered with a decorative cover plate 11 which can be broken by the ballistic rocket 13, to ensure the overall appearance of the fuselage.

[0042] In this embodiment, the rocket mounting seat 12 is independently arranged in the support structure 9, located on the left side of the parachute bag 6, the ballistic rocket 13 adopts the product BRS-440 of the BRS Aerospace Company, arranged on the rocket mounting seat 12, the ballistic rocket 13 is connected with the parachute, and the ballistic rocket 13 takes out the parachute after being launched.

[0043] In this embodiment, the launching trajectory of the ballistic rocket 13 is towards the top of the support structure 9, the launching trajectory forms an angle of 23° with the vertical plane where the front propeller 10 on the top of the fuselage is located, so that the parachute taken out by the ballistic rocket 13 avoids the front propeller 10.

[0044] In this embodiment, the tail of the ballistic rocket 13 is connected with the trigger cable 131, the trigger cable 131 is connected with the trigger handle 132, the trigger handle 132 extends into the cockpit so that the pilot can directly operate.

[0045] In this embodiment, the length of the main cable 7 is configured according to the attitude of the fuselage, the main cable 7 is stored on the fuselage when it is not stretched out, and the surface is covered with a decorative material 14 which is different from the skin of the fuselage so that the operator can accurately find the arrangement path of the main cable 7.

[0046] As shown in Figure 10 , in this embodiment, when the pilot judges that the parachute descent system must be used in the emergency situation encountered during the flight of the aircraft, the trigger handle 132 is pulled to activate the whole lifesaving system to open and then deploy the parachute, so as to effectively reduce the descent speed of the aircraft and significantly improve the success rate of lifesaving.

[0047] In the application, the extension section of the left main wing beam 301 of the left wing 3 and the right main wing beam 401 of the right wing 4 are connected with the fuselage main frame 1 through high-strength pins 5, the high-strength pins 5 at the connection points are used as front hanging points, the characteristics of high local structure bearing are effectively utilized, and the large overload coefficient load caused by the landing parachute when it is ejected and unfolded is borne; in cooperation with the rear hanging points, the arrangement of front two and rear one hanging points is presented, the stable attitude of the whole machine hanging is formed, and the trajectory of the trajectory rocket 13 and the landing parachute is adjusted to avoid the working range of the front propeller 10, so that the possibility that the landing parachute is damaged by being cut by the blades after being taken out of the fuselage is significantly reduced.

Claims

1. A whole machine ballistic parachute rescue system of a light amphibious sports aircraft, comprising a sandwich type main frame of the machine body and a longitudinal load-bearing machine body, characterized in that: The fuselage main frame is staggered with detachable left wing and right wing, high-strength pins are penetrated between the fuselage main frame, left wing and right wing, and the high-strength pins are respectively opposite on both sides of the fuselage main frame as the front suspension point of the parachute; The fuselage main frame comprises fuselage front main frame and fuselage rear main frame arranged in front and back, and the left wing and right wing are staggered between the fuselage front main frame and the fuselage rear main frame; The longitudinal bearing fuselage frame is arranged along the axis of the moving airplane at the rear of the fuselage main frame, and the rear suspension point of the parachute is arranged on the longitudinal bearing fuselage frame; The parachute is connected with the front suspension point and the rear suspension point through the main cable, and the parachute is arranged in the parachute bag, which is arranged between the fuselage main frame and the longitudinal bearing fuselage frame; Rocket mounting seat is arranged on any side of the parachute bag, and ballistic rocket is arranged on the rocket mounting seat, the ballistic rocket is connected with the parachute in the parachute bag, and the ballistic rocket takes out the parachute in the parachute bag after being launched.

2. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: The left main spar of the left wing extends from the wing root to the right wing direction until it extends into the wing root between the fuselage front main frame or the fuselage rear main frame and the right wing, and the high-strength pins are sequentially penetrated through the fuselage front main frame, the left main spar, the right wing and the fuselage rear main frame or the fuselage front main frame, the right wing, the left main spar and the fuselage rear main frame.

3. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: The right main spar of the right wing extends from the wing root to the left wing direction until it extends into the wing root between the fuselage front main frame or the fuselage rear main frame and the left wing, and the high-strength pins are sequentially penetrated through the fuselage front main frame, the right main spar, the left wing and the fuselage rear main frame or the fuselage front main frame, the left wing, the right main spar and the fuselage rear main frame.

4. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: Supporting structure for bearing the parachute bag is arranged between the fuselage main frame and the longitudinal bearing fuselage frame, the supporting structure is arranged on the fuselage between the fuselage main frame and the longitudinal bearing fuselage frame, and the supporting structure comprises support one and support two, which bear the parachute bag and make the parachute bag form an angle with the front propeller on the top of the fuselage.

5. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 4, characterized in that: An opening is arranged on the skin of the fuselage corresponding to the top of the supporting structure, and a decorative cover plate is arranged on the opening.

6. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 4, characterized in that: The rocket mounting seat is independently arranged in the supporting structure and located on any side of the parachute bag, the launch trajectory of the ballistic rocket is towards the top of the supporting structure, the launch trajectory forms an angle with the vertical plane where the front propeller on the top of the fuselage is located, so that the parachute taken out by the ballistic rocket avoids the front propeller.

7. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: The tail of the ballistic rocket is connected with a trigger cable, the trigger cable is connected with a trigger handle, and the trigger handle extends into the cockpit so that the pilot can directly operate.

8. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: A U-shaped connecting piece is fixedly arranged on the rear suspension point, and the main cable is fixedly connected with the rear suspension point through the U-shaped connecting piece.

9. The overall ballistic parachute rescue system of a light amphibious sports aircraft according to claim 1, characterized in that: The length of the main cable is configured according to the body posture, the main cable is stored on the fuselage when it is not stretched out, and the surface is covered with decorative material, which is different from the fuselage skin so that the operator can accurately find the arrangement path of the main cable.

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