Aircraft parachute system suitable for small general-purpose aircraft

Abstract

The aircraft parachute system comprises a whole aircraft parachute assembly and an installation assembly, and the installation assembly comprises an aircraft body structure 1, a connecting point 2, a parachute cabin opening frame 5, a parachute cabin 6, a parachute cabin bottom 6a, a lower support 11, an auxiliary fixing point 13, an aircraft floor 14, a control handle support 15, a central control console 17 and a parachute pack mooring point 18; the complete parachute assembly comprises a transfer belt 3, a parachute bag 7, a complete parachute 8, a parachute cord connecting ring 9, a parachute shooting rocket 10, a control inhaul cable 12 and a control handle 16; four connecting points 2 are arranged at connecting joints of wings and a fuselage, a vertical shaft type parachute bay 6 is arranged in a luggage compartment of the aircraft, a complete machine parachute 8 and a parachute shooting rocket 10 are installed in the parachute bay 6, and four transfer belts 3 are laid between the complete machine parachute 8 and the connecting points 2 along the outer surface of the fuselage; a control handle 16 is arranged at the position close to an aircraft central control board 17, and an ignition inhaul cable 12 is laid between the control handle 16 and the parachute shooting rocket 10 along an aircraft floor 14.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of general aviation safety, and particularly relates to an airplane parachute system suitable for small general airplanes. BACKGROUND

[0002] The whole machine parachute is a safety device for protecting aircraft. It is usually composed of parachute opening power, large parachute and related connection system, and can slow down the whole aircraft and land safely in an emergency.

[0003] In recent years, the development of general aviation has accelerated, and unmanned cargo aircraft, flying cars and other concepts have emerged. In order to protect the safety of personnel and high-value goods on board, advanced general aircraft and other aircraft are equipped with whole machine parachutes to improve product performance and market competitiveness. However, early general aircrafts are less equipped with this safety device, and in order to improve the safety of such general aircrafts, the whole machine parachute needs to be modified.

[0004] According to the parachute vertical lifesaving specification, the whole machine parachute needs to reduce the falling speed of the aircraft to not more than 7 meters per second. For aircrafts with large weight, large area and weight parachutes must be equipped, and the technical and economic nature needs to be comprehensively considered. The whole machine parachute currently provided on the market is suitable for aircrafts with a mass of not more than 2000 kg. SUMMARY

[0005] The purpose of the application is to provide an airplane parachute system suitable for small general airplanes, which can solve the problem of low safety of existing general airplanes.

[0006] Technical scheme: An airplane parachute system suitable for small general airplanes, comprising a whole machine parachute assembly and a mounting assembly, wherein:

[0007] The mounting assembly comprises a machine body structure 1, a connection point 2, a parachute hatch frame 5, a parachute cabin 6, a parachute cabin bottom 6a, a lower support 11, an auxiliary fixing point 13, an airplane floor 14, a control handle support 15, a central control table 17, a parachute bag retaining point 18, wherein the machine body structure 1 comprises a wing and a fuselage; the whole machine parachute assembly comprises an adapter belt 3, a parachute bag 7, a whole machine parachute 8, a parachute rope connecting ring 9, a parachute shooting rocket 10, a control cable 12 and a control handle 16;

[0008] Four connection points 2 are arranged at the wing and fuselage connection joint, a vertical shaft type parachute cabin 6 is arranged in the luggage compartment of the airplane, the whole machine parachute 8 and the parachute shooting rocket 10 are installed in the parachute cabin 6, and four adapter belts 3 are laid along the outer surface of the fuselage between the whole machine parachute 8 and the connection points 2; a control handle 16 is arranged near the central control table 17 of the airplane, and a firing cable 12 is laid along the airplane floor 14 between the control handle 16 and the parachute shooting rocket 10.

[0009] Specifically, the four connection points 2 are arranged at the connection joints of the front and rear reinforced frames of the fuselage and the front and rear beams of the wings.

[0010] Specifically, the cross-sectional shape of the parachute cabin 6 is set according to the combined shape of the whole machine parachute 8 and the parachute rocket 10; a hole is opened on the upper surface structure of the fuselage according to the intersection line of the cross section of the parachute cabin 6 and the upper surface of the fuselage, and a parachute cabin opening frame 5 is added for structural reinforcement; the upper end of the parachute cabin 6 is connected with the parachute cabin opening frame 5, and the lower end of the parachute cabin 6 is connected with the aircraft floor 14 through the lower support 11; the lower part of the parachute cabin cylinder is closed by the parachute cabin bottom 6a to support the whole machine parachute 8, and the upper opening of the parachute cabin is covered by the parachute cabin cover 4.

[0011] Specifically, the four adapter belts 3 are fixed on the outer surface of the aircraft structure 1 in two groups of left and right.

[0012] Specifically, the control handle 16 is rigidly fixed on the aircraft structure by the control handle support 15; the ignition cable 12 is fixed on the original aircraft structure by the auxiliary fixing point 13; a hole is opened on the parachute cabin bottom 6a when installing the handle and the cable to pass through the ignition cable 12.

[0013] Specifically, the parachute rope connecting ring 9 and the adapter belt 3 are stored in the gap between the parachute bag and the cylinder, and are properly tied to prevent them from blocking the parachute rocket 10 from pulling out the whole machine parachute 8; the parachute bag is tied and fixed on the cylinder wall of the parachute cabin 6 by adding a tie point on the reinforcing belt of the side wall of the parachute bag 7.

[0014] In summary, the present application is to make up for the lack of emergency safety measures for small general aircrafts without whole machine parachutes, and innovatively proposes a whole machine parachute suitable for small general aircrafts, which effectively improves the safety of such aircrafts. The present application provides a technically feasible and economically practical solution for modifying small general aircrafts with whole machine parachutes. According to the existing layout of small general aircrafts, the parachute connection points and the parachute cabin are reasonably set to realize the integrated installation of the whole machine parachute system with minimal modification. The parachute connection points use the original load-bearing structure, which simplifies the structural reinforcement modification; the parachute cabin adopts an embedded structure without changing the original aircraft aerodynamic shape; the connecting belt is fixed tightly to the surface of the aircraft body to avoid damaging the aircraft skin. Strictly following the product manual for installation and use, the safety of the system is ensured; the parachute opening procedure is verified through ground tests to ensure the reliability of the whole machine parachute system. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 A structure diagram of an aircraft parachute system suitable for small general aircrafts is provided for the present application;

[0016] Figure 2 A structure diagram of a whole machine parachute is provided for the present application;

[0017] Figure 3This invention provides an installation diagram of a parachute pack with the parachute compartment tube removed inside the parachute compartment.

[0018] Among them, 1-aircraft structure, 2-connection point, 3-transfer belt, 5-parachute compartment frame, 6-parachute compartment, 6a-parachute compartment bottom, 7-parachute bag, 8-complete aircraft parachute, 9-parachute line connecting ring, 10-parachute rocket, 11-lower support, 12-control cable, 13-auxiliary fixing point, 14-aircraft floor, 15-control handle bracket, 16-control handle, 17-central control panel, 18-parachute bag mooring point. Detailed Implementation

[0019] Example 1

[0020] like Figure 1 As shown, this application provides an aircraft parachute system suitable for small general aviation aircraft, including an overall parachute assembly and an installation assembly, wherein:

[0021] The installation components include fuselage structure 1, connection point 2, parachute compartment frame 5, parachute compartment 6, parachute compartment bottom 6a, lower support 11, auxiliary fixing point 13, aircraft floor 14, control handle bracket 15, central control console 17, and parachute tie-down point 18. The fuselage structure 1 includes wings and fuselage.

[0022] The complete parachute assembly includes an adapter belt 3, a parachute bag 7, a complete parachute 8, a parachute rope connecting ring 9, a parachute rocket 10, a control cable 12, and a control handle 16;

[0023] Four connection points 2 are arranged at the wing-fuselage connection joint. A vertical parachute compartment 6 is arranged in the aircraft's baggage compartment. The whole aircraft parachute 8 and the parachute rocket 10 are installed in the parachute compartment 6. Four adapter straps 3 are laid along the outer surface of the fuselage between the whole aircraft parachute 8 and the connection point 2. A control handle 16 is arranged and installed near the central control panel 17 of the aircraft. An ignition cable 12 is laid along the aircraft floor 14 between the control handle 16 and the parachute rocket 10.

[0024] Specifically, the four connection points 2 are respectively located at the connection joints between the front and rear reinforcing frames of the fuselage and the front and rear spars of the wings.

[0025] Specifically, the cross-sectional shape of the parachute compartment 6 is set according to the combined shape of the parachute 8 and the parachute rocket 10; according to the intersection line between the cross-section of the parachute compartment 6 and the upper surface of the fuselage, a hole is opened on the upper surface structure of the fuselage, and a parachute compartment frame 5 is added for structural reinforcement. The upper end of the parachute compartment 6 is connected to the parachute compartment frame 5, and the lower end of the parachute compartment is connected to the aircraft floor 14 through the lower support 11; the lower end of the parachute compartment is closed by the parachute compartment bottom 6a to support the parachute 8 of the whole aircraft, and the upper opening of the parachute compartment is covered by the parachute compartment cover 4.

[0026] In practical applications, a gap of no less than 20 mm is reserved between the parachute compartment 6 and the assembly to ensure a smooth parachute opening process.

[0027] In practical application, the depth of the parachute bay should ensure that the distance between the top of the ejection rocket 10 and the parachute bay cover 4 is not less than 50mm in the installed state.

[0028] In practical application, the connection of the cover adopts multi-point gluing or multi-section adhesive bonding, and the bonding strength is not greater than 15kgf.

[0029] Specifically, the four adapter belts 3 are fixed by being pasted or tethered on the outer surface of the body structure 1.

[0030] It should be noted that the pasting or tethering connection strength should ensure that the adapter belt does not come off during flight, and can be smoothly released during parachute opening.

[0031] Specifically, the operating handle 16 is rigidly fixed on the aircraft structure by using the operating handle support 15; the ignition cable 12 is fixed on the original aircraft structure by using the auxiliary fixing point 13; when the handle and the cable are installed, a hole is opened on the parachute bay bottom 6a to pass through the ignition cable 12.

[0032] In practical application, the ignition cable 12 can be fixed on the original aircraft structure by using a clamp connection or an adhesive fixing mode.

[0033] Specifically, as shown in Figure 2 The whole machine parachute 8 is folded, compressed and packaged in the rectangular cross-section parachute bag 7; the front and rear walls of the parachute bag 7 are reserved with reinforcing belts for tethering and fixing the parachute package; a small section of parachute rope is reserved outside the parachute package, connected with the four adapter belts 3 through the parachute rope connecting ring 9, and the parachute rope connecting ring 9 adopts a melon buckle or other metal ring. The ejection rocket 10 is bound and fixed on the side wall of the parachute package, or independently installed on the parachute bay structure; the ejection rocket 10 adopts a pull fire type detonator ignition and a boding cable control, and the boding cable outer sleeve is fixed; the operating handle 16 moves relative to the outer sleeve of the center cable, and a relative displacement of more than 5cm triggers the pull fire type detonator to complete the rocket ignition.

[0034] Specifically, as shown in Figure 3 The parachute rope connecting ring 9 and the adapter belt 3 are accommodated in the gap between the parachute package and the cylinder, and are properly tethered to prevent them from blocking the ejection rocket from pulling out the whole machine parachute 8; the parachute package is tethered and fixed on the cylinder wall of the parachute bay 6 by adding a tethering point on the reinforcing belt of the side wall of the parachute bag 7.

[0035] Embodiment two

[0036] The purpose of the present application is to provide an aircraft parachute system suitable for small general aircraft, including whole machine parachute selection, whole machine parachute system on-board layout, parachute connection point structure modification, parachute package and ejection rocket installation, connection belt installation, operating device installation, etc.

[0037] Whole machine parachute selection scheme: according to the take-off weight, flight speed, flight height and other parameters of the small general aircraft, the appropriate size of the whole machine parachute system is selected to ensure the safe landing speed in the predetermined use environment. The whole machine parachute system selects the customized product provided by the professional supplier, and the whole machine parachute generally adopts the mechanical type trigger rocket parachute opening. The whole machine parachute used should meet the requirements of ASTM F2316-12 "Machine Emergency Parachute Specification".

[0038] Whole machine parachute system on-board layout scheme: according to the existing layout of the small general aircraft, the connecting point is arranged at the load bearing structure of the machine body to bear the parachute load. After the position of the connecting point is determined, the length of the connecting belt is adjusted to ensure that the aircraft can land at a nose-down 15°-30° attitude. The opening is arranged on the wall plate of the machine body, and the parachute compartment is arranged inside the machine body to install the parachute bag and the rocket. The installation of the parachute bag and the rocket should ensure that the parachute bag is ejected without obstacles and the parachute rope is fully stretched. The adapter belt is laid between the parachute bag and the connecting point. The parachute opening control handle is arranged near the pilot. The pull cable is laid between the control handle and the rocket.

[0039] Parachute connecting point structure modification: the connecting point of the parachute and the machine body structure should be able to bear the dynamic load in the parachute opening process and the parachute load in the stable landing process. The connecting point is generally selected at the joint of the wing and the fuselage, the reinforcing frame and other parts, and the joint suitable for the connecting belt is arranged. After the size and direction of the parachute load are determined, the strength calculation is required to verify that the structure strength of the parachute connecting point meets the bearing requirements, and the original machine structure is appropriately strengthened if necessary.

[0040] Parachute bag and rocket installation: the parachute bag and the rocket are combined into one by the supplier, and the aircraft needs to provide installation space and support structure for the parachute bag and the rocket. The parachute bag and the rocket are installed by opening the hatch on the surface of the machine body and arranging the parachute compartment inside the machine body. The hatch is opened on the surface structure of the machine body, and the structure is reinforced by adding the mouth frame, which also serves as the installation structure of the parachute compartment. The parachute compartment adopts a vertical shaft type structure, and the bottom of the parachute compartment is closed to support the weight of the parachute bag. The parachute compartment and the parachute bag and the rocket should have enough clearance around them to ensure that the parachute bag can smoothly exit the compartment without interfering with the parachute compartment. The outer cover of the parachute bag is connected and fixed with the side wall of the parachute compartment by using a support to prevent the parachute bag from moving or tilting in the parachute compartment. The hatch opening is closed with a hatch cover to prevent the parachute bag from being contaminated. The connection strength of the hatch cover and the mouth frame meets the product installation requirements, and the hatch cover is knocked off by the rocket thrust during parachute opening. The installation should ensure that the space between the top of the rocket and the hatch cover is not less than 50mm to ensure the smooth start of the rocket.

[0041] Connecting strap installation: connecting strap is used to connect parachute connecting point and parachute rope, distributing parachute load to airframe structure. In order to avoid damaging airframe structure, connecting strap is pasted or tied close to airframe surface, and is opened in sequence during parachute opening process. Excess connecting strap and its connecting point with parachute rope should be properly stored in parachute bay to prevent blocking parachute opening.

[0042] Manipulation device installation: mechanically triggered manipulation device includes handle and pull cable, handle should be arranged at a position convenient for pilot to operate, and measures should be taken to prevent accidental triggering. Mounting bracket of handle should be rigidly fixed to prevent failure to trigger normally. Displacement of handle is transmitted to ignition component of ejection rocket through pull cable, and laying path of pull cable should be as straight as possible, and minimum bending radius is not less than 10 times of pull cable diameter.

[0043] In summary, the application is to make up for the lack of emergency safety measures of small general aircraft without whole machine parachute, and innovatively proposes a whole machine parachute suitable for small general aircraft, which effectively improves the safety of such aircraft. The application provides a technically feasible and economically practical solution for retrofitting whole machine parachute for small general aircraft. According to the existing layout of small general aircraft, the parachute connecting point and parachute bay are reasonably set to realize integrated installation of whole machine parachute system with minimum modification. The parachute connecting point uses original load-bearing structure, which simplifies the structural reinforcement modification; the parachute bay adopts embedded structure, which does not change the original aerodynamic shape; the connecting strap is fixed close to the surface of the aircraft body to avoid damaging the airframe skin. Strictly according to the product manual for installation and use, the safety of the system is ensured; the parachute opening process is verified through ground test to ensure the reliability of the whole machine parachute system.

Claims

1. A parachute system for small general aviation aircraft, characterized in that, Includes the complete parachute assembly and mounting components, of which: The installation components include the fuselage structure (1), connection points (2), parachute compartment frame (5), parachute compartment (6), parachute compartment bottom (6a), lower support (11), auxiliary fixing points (13), aircraft floor (14), control handle bracket (15), central control console (17), and parachute pack tethering point (18). The fuselage structure (1) includes the wings and fuselage. The whole aircraft parachute assembly includes the adapter belt (3), parachute bag (7), whole aircraft parachute (8), parachute line connecting ring (9), parachute rocket (10), control cable (12), and control handle (16). Four connection points (2) are arranged at the wing-fuselage connection joint. A vertical parachute compartment (6) is arranged in the baggage compartment of the aircraft. The whole aircraft parachute (8) and the parachute rocket (10) are installed in the parachute compartment (6). Four adapter belts (3) are laid along the outer surface of the fuselage between the whole aircraft parachute (8) and the connection point (2). A control handle (16) is arranged and installed near the central control panel (17) of the aircraft. An ignition cable (12) is laid along the aircraft floor (14) between the control handle (16) and the parachute rocket (10).

2. The aircraft parachute system according to claim 1, characterized in that, The four connection points (2) are respectively located at the connection joints between the front and rear reinforcing frames of the fuselage and the front and rear beams of the wing.

3. The aircraft parachute system according to claim 1, characterized in that, The cross-sectional shape of the parachute compartment (6) is set according to the combined shape of the whole parachute (8) and the parachute rocket (10); according to the intersection line of the cross-section of the parachute compartment (6) and the upper surface of the fuselage, holes are opened on the upper surface structure of the fuselage, and the parachute compartment frame (5) is added for structural reinforcement. The upper end of the parachute compartment (6) is connected to the parachute compartment frame (5), and the lower end of the parachute compartment is connected to the aircraft floor (14) through the lower support (11); the lower end of the parachute compartment is closed by the parachute compartment bottom (6a) to support the whole parachute (8), and the upper opening of the parachute compartment is covered by the parachute compartment cover (4).

4. The aircraft parachute system according to claim 1, characterized in that, Four adapter straps (3) are attached or tied to the outer surface of the body structure (1) in two groups, left and right.

5. The aircraft parachute system according to claim 1, characterized in that, The control handle (16) is rigidly fixed to the aircraft structure using the control handle bracket (15); the ignition cable (12) is fixed to the original aircraft structure using the auxiliary fixing point (13); when installing the handle and cable, a hole is made on the bottom (6a) of the parachute compartment to pass through the ignition cable (12).

6. The aircraft parachute system according to claim 1, characterized in that, The parachute rope connecting ring (9) and the adapter belt (3) are stored in the gap between the parachute pack and the tube body and properly secured to prevent them from blocking the parachute rocket from pulling out the whole parachute (8); by adding a tethering point to the reinforcing belt on the side wall of the parachute pack (7), the parachute pack is secured to the tube wall of the parachute compartment (6).

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