CN215245551U - Light aircraft integrated with complete machine life-saving parachute system - Google Patents
Light aircraft integrated with complete machine life-saving parachute system Download PDFInfo
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- CN215245551U CN215245551U CN202121394001.0U CN202121394001U CN215245551U CN 215245551 U CN215245551 U CN 215245551U CN 202121394001 U CN202121394001 U CN 202121394001U CN 215245551 U CN215245551 U CN 215245551U
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Abstract
The utility model relates to a light aircraft integrated with a complete machine lifesaving parachute system, which comprises an aircraft bracket, a complete machine lifesaving parachute system and an aircraft skin covering the aircraft bracket, wherein the aircraft bracket comprises an aircraft keel, a main undercarriage and a cabin bracket, the main undercarriage is connected with the middle part of the aircraft keel, and the cabin bracket is connected with the top part of the aircraft keel; the whole lifesaving parachute system comprises a projectile, a parachute pack and an operating handle, wherein the projectile and the parachute pack are integrated at the rear end of the cabin bracket, a lifesaving parachute is arranged in the parachute pack, a parachute rope of the lifesaving parachute is fixed at the top of the cabin bracket, and the operating handle is arranged in the aircraft cockpit and connected to the projectile; the aircraft skin is provided with a parachute window at the position above the parachute pack, and the parachute window can be opened when the parachute is popped up. The light aircraft can open the whole lifesaving parachute when encountering emergency, so that the aircraft is sent back to the ground at a lower speed, the safety of the aircraft is greatly improved, and the life safety of passengers is ensured.
Description
Technical Field
The utility model belongs to the technical field of light aircraft, concretely relates to integrated light aircraft that has complete machine lifesaving parachute system.
Background
With the economic development, the number of light airplanes in China is continuously increased, the application range is continuously expanded, and the safety of the light airplane is widely noted. The light airplane has the advantages of low purchase and operation cost and simple and convenient maintenance, is widely applied to aspects of license training, private flight, sightseeing and traveling, aviation mapping and the like, and plays a significant role in the general aviation market.
However, the light aircraft has no high safety of civil aircrafts and no seat ejection lifesaving system of fighters, so that the light aircraft has no reliable lifesaving equipment in the event of an accident. Therefore, the development of a safety lifesaving system suitable for a light airplane is accelerating.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems in the prior art, the utility model provides a light aircraft integrated with a complete life-saving parachute system. The to-be-solved technical problem of the utility model is realized through following technical scheme:
the utility model provides a light aircraft integrated with a complete life-saving parachute system, which comprises an aircraft bracket, a complete life-saving parachute system and an aircraft skin coated outside the aircraft bracket, wherein,
the aircraft support comprises an aircraft keel, a main landing gear and a cabin support, the aircraft keel is arranged along the length direction of an aircraft, the main landing gear is connected to the middle part of the aircraft keel, and the cabin support is connected to the top of the aircraft keel;
the whole lifesaving parachute system comprises a projectile, a parachute pack and an operating handle, wherein the projectile and the parachute pack are integrated at the rear end of the cabin bracket, a lifesaving parachute is arranged in the parachute pack, a parachute rope of the lifesaving parachute is fixed at the top of the cabin bracket, and the operating handle is arranged in an aircraft cockpit and connected to the projectile and used for driving an parachute body of the lifesaving parachute to pop out of the parachute pack through the projectile;
the aircraft skin is provided with a closed parachute window at a position above the parachute pack, and the parachute window can be opened under the action of the projectile so that the parachute penetrates out of the aircraft skin.
In one embodiment of the present invention, the main landing gear includes a first main landing gear beam and a second main landing gear beam symmetrically disposed on both sides of the aircraft keel.
In one embodiment of the present invention, the first main landing gear beam and the second main landing gear beam are connected to the side wall of the aircraft keel by right angle brackets, respectively.
In one embodiment of the present invention, the cabin bracket comprises a triangular support frame, a first support bar, a second support bar, a third support bar, a fourth support bar, a fifth support bar and a sixth support bar, wherein,
the triangular support frame is of an isosceles triangular structure and comprises a top angle, a first bottom angle and a second bottom angle, and the top angle is connected to the front end of the airplane keel through the first support rod; the first bottom corner is connected to the free end of the first main landing gear beam and the tail end of the airplane keel through the second supporting rod and the third supporting rod respectively; the second base angle is connected to the free end of the first main landing gear beam, the free end of the second main landing gear beam and the tail end of the aircraft keel through the fourth supporting rod, the fifth supporting rod and the sixth supporting rod respectively.
In one embodiment of the present invention, the parachute comprises three parachute cords connected to the parachute body, the three parachute cords are respectively connected to the top angle, the first base angle and the second base angle of the triangular support frame.
In one embodiment of the present invention, the parachute package is fixed to the third support rod and the sixth support rod at the same time, and the projectile is fixed to the third support rod.
In one embodiment of the present invention, the aircraft keel is a hollow aluminum alloy cylinder structure.
Compared with the prior art, the beneficial effects of the utility model reside in that:
the utility model provides an integrated light aircraft that has complete machine lifesaving parachute system can open complete machine lifesaving parachute when meeting with emergency to send the aircraft back ground with lower speed, very big improvement the aircraft security, guarantee passenger's life safety.
Drawings
Fig. 1 is a schematic structural diagram of a light aircraft integrated with a complete life-saving parachute system according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a projectile according to an embodiment of the present invention;
fig. 3 is a schematic view of a lifesaving process of a light aircraft integrated with a complete life saving parachute system according to an embodiment of the present invention.
Description of reference numerals:
1-aircraft keel; 2-main landing gear; 21-a first main landing gear cross member; 22-a second main landing gear cross member; 3-a cabin bracket; 31-a triangular support frame; 311-top angle; 312-a first base angle; 313-a second base angle; 32-a first support bar; 33-a second support bar; 34-a third support bar; 35-a fourth support bar; 36-a fifth support bar; 37-a sixth support bar; 4-projectile projectiles; 41-top cover; 5-umbrella bag; 6-right angle brackets; 7-umbrella bag hauling rope.
Detailed Description
In order to further explain the technical means and effects of the present invention adopted to achieve the predetermined objects, a light aircraft integrated with a complete life-saving parachute system according to the present invention will be described in detail with reference to the accompanying drawings and the detailed description.
The foregoing and other technical matters, features and effects of the present invention will be apparent from the following detailed description of the embodiments, which is to be read in connection with the accompanying drawings. The technical means and effects of the present invention adopted to achieve the predetermined purpose can be more deeply and specifically understood through the description of the specific embodiments, however, the attached drawings are provided for reference and description only and are not used for limiting the technical scheme of the present invention.
Referring to fig. 1 and 2, fig. 1 is a schematic structural diagram of a light aircraft integrated with a complete life saving parachute system according to an embodiment of the present invention, and fig. 2 is a schematic structural diagram of a projectile according to an embodiment of the present invention. The lightweight aircraft comprises an aircraft frame, a complete life saving parachute system and an aircraft skin (not shown in the attached drawings) covering the exterior of the aircraft frame. The aircraft support comprises an aircraft keel 1, a main undercarriage 2 and a cabin support 3, wherein the aircraft keel 1 is arranged along the length direction of an aircraft and is parallel to the ground, the main undercarriage 2 is connected to the middle of the aircraft keel 1, and the cabin support 3 is connected to the top of the aircraft keel 1. In this embodiment, the aircraft keel 1 is a hollow aluminum alloy cylindrical structure.
The whole lifesaving parachute system comprises a projectile 4, a parachute pack 5 and an operating handle, wherein the projectile 4 and the parachute pack 5 are integrated at the rear end of a cabin support 3, a lifesaving parachute is arranged in the parachute pack 5, a parachute rope of the lifesaving parachute is fixed to the top of the cabin support 3, and the operating handle is arranged in an aircraft cockpit and connected to the projectile 4 and used for driving a parachute body of the lifesaving parachute to pop out of the parachute pack 5 through controlling the projectile 4. Specifically, the projectile bomb 4 is provided with a parachute package traction rope 7, the first end of the parachute package traction rope 7 is connected with the top cover 41 of the projectile bomb 4, and the second end of the parachute package traction rope is connected with the parachute body of the lifesaving parachute.
Further, a parachute window is arranged on the aircraft skin above the parachute pack 5, the parachute window is in a closed state in the normal flight state of the aircraft and can be opened under the action of the projectile 4, and the parachute penetrates out of the aircraft skin.
Specifically, the projectile 4 is filled with a solid composite propellant, an ignition device in the projectile 4 is started and releases sparks when a pilot pulls an operating handle, the sparks ignite the solid composite propellant through a jet orifice, the solid composite propellant rapidly releases chemical energy and is heated and expanded to eject a top cover 41 of the projectile 4 at a high speed, the impact force ejected from the top cover 41 pushes open a window of a lifesaving parachute on an upper cover, a parachute pack traction rope 7 connected with the top cover 41 is taken out of the plane body along with the parachute, and then the parachute pack traction rope 7 together with the lifesaving parachute is ejected out of the plane body from the parachute pack 5. It is emphasized that the solid composite propellant uses stored chemical energy to provide the necessary thrust to quickly remove the housing cover and to carry the parachute out of the parachute bag. The solid composite propellant of the present embodiment includes a heterogeneous mixture of Ammonium Perchlorate (AP) and aluminum powder (Al), an oxidizer, and a fuel.
The main landing gear 2 comprises a first main landing gear cross member 21 and a second main landing gear cross member 22 symmetrically disposed on either side of the aircraft keel 1. In the present exemplary embodiment, the first main landing gear cross member 21 and the second main landing gear cross member 22 are each fastened to a side wall of the aircraft keel 1 by means of a right-angled bracket 6.
As shown in fig. 1, the cabin bracket 3 of the present embodiment includes a triangular support frame 31, a first support rod 32, a second support rod 33, a third support rod 34, a fourth support rod 35, a fifth support rod 36 and a sixth support rod 37, wherein the triangular support frame 31 is in an isosceles triangle structure and includes a top corner 311, a first bottom corner 312 and a second bottom corner 313, and the top corner 311 is connected to the front end of the aircraft keel 1 through the first support rod 32; the first bottom corner 312 is connected to the free end of the first main landing gear beam 21 and the tail end of the aircraft keel 1 through the second support bar 33 and the third support bar 34, respectively; the second bottom corner 313 is connected to the free end of the first main landing gear cross member 21, the free end of the second main landing gear cross member 22 and the aft end of the aircraft keel 1 by means of a fourth support bar 35, a fifth support bar 36 and a sixth support bar 37 respectively.
Specifically, the triangular support frame 31, the first support bar 32, the second support bar 33, the fourth support bar 35 and the fifth support bar 36 together enclose a space of a cockpit, and the second support bar 33, the third support bar 34, the fourth support bar 35, the fifth support bar 36 and the sixth support bar 37 together enclose a space of a luggage compartment.
The parachute of the embodiment comprises three parachute ropes connected to the parachute body, and the other ends of the three parachute ropes are respectively connected to the top angle 311, the first bottom angle 312 and the second bottom angle 313 of the triangular support frame, so that the center of gravity of the airplane is ensured to be stable when the parachute is unfolded and the airplane is decelerated.
Further, the bag 5 is fixed to both the third support bar 34 and the sixth support bar 37, and the projectile 4 is fixed to the third support bar 34 by suitable fasteners. In this embodiment, one side of the lower surface of the umbrella bag 5 is tied to the third support bar 34, and the other side of the lower surface of the umbrella bag 5 is tied to the sixth support bar 37, so that the umbrella bag 5 is erected between the third support bar 34 and the sixth support bar 37. In the actual use process, the size, material and the like of the parachute used can be selected according to specific parameters such as the total weight of the airplane and the like.
Referring to fig. 3, fig. 3 is a schematic view of a lifesaving process of a light aircraft integrated with a complete life saving parachute system according to an embodiment of the present invention. When the airplane is in danger, a pilot in a cockpit manually controls the operating handle, an ignition device in the projectile bomb 4 is started and releases sparks, the sparks ignite the solid composite propellant through the jet orifice, the solid composite propellant rapidly releases chemical energy, the solid composite propellant is heated and expanded, a top cover 41 of the projectile bomb 4 is ejected at a high speed, the impact force ejected from the top cover 41 rushes open a window of the lifesaving umbrella on an upper covering, and meanwhile, an umbrella body of the lifesaving umbrella is taken out of an umbrella bag 5, so that the whole umbrella body is ejected out of the airplane, and the umbrella body is rapidly unfolded under the action of airflow.
The light airplane integrated with the whole lifesaving parachute system can open the whole lifesaving parachute when encountering an emergency, so that the airplane is sent back to the ground at a lower speed, the safety of the airplane is greatly improved, and the life safety of passengers is guaranteed.
The foregoing is a more detailed description of the present invention, taken in conjunction with the specific preferred embodiments thereof, and it is not intended that the invention be limited to the specific embodiments shown and described. To the utility model belongs to the technical field of ordinary technical personnel, do not deviate from the utility model discloses under the prerequisite of design, can also make a plurality of simple deductions or replacement, all should regard as belonging to the utility model discloses a protection scope.
Claims (7)
1. A light aircraft integrated with a complete machine parachute system is characterized by comprising an aircraft bracket, the complete machine parachute system and an aircraft skin covering the outside of the aircraft bracket, wherein,
the aircraft support comprises an aircraft keel (1), a main landing gear (2) and a cabin support (3), wherein the aircraft keel (1) is arranged along the length direction of an aircraft, the main landing gear (2) is connected to the middle of the aircraft keel (1), and the cabin support (3) is connected to the top of the aircraft keel (1);
the whole lifesaving parachute system comprises a projectile (4), a parachute pack (5) and an operating handle, wherein the projectile (4) and the parachute pack (5) are integrated at the rear end of the cabin bracket (3), a lifesaving parachute is arranged in the parachute pack (5), a parachute rope of the lifesaving parachute is fixed to the top of the cabin bracket (3), and the operating handle is arranged in an aircraft cockpit and connected to the projectile (4) and used for driving an parachute body of the lifesaving parachute to pop out of the parachute pack (5) through the projectile (4);
the aircraft skin is provided with a closed parachute window at a position above the parachute pack (5), and the parachute window can be opened under the action of the projectile (4) so that the parachute penetrates out of the aircraft skin.
2. The light aircraft integrated with a complete life saving parachute system as claimed in claim 1, wherein the main landing gear (2) comprises a first main landing gear cross member (21) and a second main landing gear cross member (22) symmetrically arranged on both sides of the aircraft keel (1).
3. The light aircraft integrated with a complete life saving parachute system as set forth in claim 2, wherein the first main landing gear cross member (21) and the second main landing gear cross member (22) are respectively connected to a side wall of the aircraft keel (1) through a right angle bracket (6).
4. The light aircraft integrated with the complete life saving parachute system as set forth in claim 2, wherein the cabin bracket (3) comprises a triangular support frame (31), a first support bar (32), a second support bar (33), a third support bar (34), a fourth support bar (35), a fifth support bar (36) and a sixth support bar (37), wherein,
the triangular support frame (31) is of an isosceles triangular structure and comprises a top angle (311), a first bottom angle (312) and a second bottom angle (313), and the top angle (311) is connected to the front end of the airplane keel (1) through the first support rod (32); the first bottom corner (312) is connected to the free end of the first main landing gear beam (21) and the tail end of the aircraft keel (1) through the second support rod (33) and the third support rod (34), respectively; the second base angle (313) is connected to the free end of the first main landing gear beam (21), the free end of the second main landing gear beam (22) and the tail end of the aircraft keel (1) by the fourth support bar (35), the fifth support bar (36) and the sixth support bar (37) respectively.
5. The light aircraft integrated with the complete life saving umbrella system as claimed in claim 4, wherein the life saving umbrella comprises three umbrella ropes connected to the umbrella body, and the three umbrella ropes are respectively connected to the top corner (311), the first bottom corner (312) and the second bottom corner (313) of the triangular support frame.
6. The light aircraft integrated with the complete life saving parachute system of claim 4, wherein the parachute package (5) is fixed on the third support rod (34) and the sixth support rod (37) at the same time, and the projectile (4) is fixed on the third support rod (34).
7. The light airplane integrated with the complete life saving umbrella system as claimed in any one of claims 1 to 6, wherein the airplane keel (1) is a hollow aluminum alloy cylindrical structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121394001.0U CN215245551U (en) | 2021-06-22 | 2021-06-22 | Light aircraft integrated with complete machine life-saving parachute system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121394001.0U CN215245551U (en) | 2021-06-22 | 2021-06-22 | Light aircraft integrated with complete machine life-saving parachute system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215245551U true CN215245551U (en) | 2021-12-21 |
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ID=79482259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121394001.0U Active CN215245551U (en) | 2021-06-22 | 2021-06-22 | Light aircraft integrated with complete machine life-saving parachute system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215245551U (en) |
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2021
- 2021-06-22 CN CN202121394001.0U patent/CN215245551U/en active Active
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