Landing and rescue system for adapted non-fully enveloped single-person aircraft

Abstract

The application provides a landing and lifesaving system for a non-fully covered single-person aircraft, which comprises a helmet for wearing, a flight suit connected with the aircraft and used for wearing, and a plurality of mechanical feet installed on the aircraft; the helmet comprises a shell and a non-triggered air cushion arranged in the shell, and a visual window is arranged on the front side of the shell; the flight suit comprises a vest, a back air bag installed on the back of the vest, a chest and abdomen air bag installed on the front of the vest, and a gas generator connected with each air bag through a pipeline, the gas generator is installed on the vest or the aircraft, and a trigger switch for inflating each air bag is arranged on the gas generator; the mechanical foot comprises a support rod, a rotating rod and a mounting block, the mounting block is connected with the aircraft, one end of the rotating rod is rotationally connected with the mounting block or the aircraft, one end of the support rod is rotationally connected with the other end of the rotating rod, and the other end of the support rod is used as a support foot. The system is used for assisting normal flight landing of the non-fully covered single-person aircraft for manned flight, and realizes forced landing and lifesaving.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of flight equipment, in particular to a landing and lifesaving system for non-fully covered single-person aircraft. BACKGROUND

[0002] Since the history recorded, the human desire for flight has never stopped. Hot air balloon, airship, glider, paraglider, aircraft, and so on, human beings are constantly pursuing more flexible, higher degree of freedom flight equipment. More and more research institutions, companies, and hobbyist teams are engaged in the research and testing of single-person aircraft from different angles.

[0003] So far, there is no landing and forced landing lifesaving system specially developed for single-person aircraft. All the research and testing mentioned above can only use the lifesaving bag of helicopter pilots, use the suspension method of helicopters, or fly on water, trying to use water to provide a guarantee for flight safety.

[0004] For flight, the take-off quality is invaluable; for manned flight, the safety of the human is the top priority; especially for non-fully covered single-person aircraft, the aircraft does not have an external support structure that completely covers the pilot.

[0005] The parachute forced landing cannot be applied to normal landing. The parachute opening condition requires certain weather and height; secondly, the ground conditions should be relatively simple, and cannot be landed in dense buildings, power lines, etc.; thirdly, there are certain requirements for the operation ability and physical strength of the pilot. Low-altitude flight, commercial flight, urban emergency rescue, and other conditions are not suitable for parachutes.

[0006] In summary, designing a landing and lifesaving system with high strength, light weight, and good safety is the most urgent problem in the development of single-person aircraft. SUMMARY

[0007] In view of the above-mentioned deficiencies of the prior art, the present application provides a landing and lifesaving system for non-fully covered single-person aircraft, which is used for assisting the normal flight landing of non-covered single-person aircraft for manned flight, and realizing forced landing and lifesaving.

[0008] In order to achieve the purpose of the present application, the following scheme is adopted:

[0009] The landing and lifesaving system for non-fully covered single-person aircraft comprises a helmet worn on the head of the pilot, a flight suit connected to the aircraft through a safety belt and worn by the pilot, and a plurality of mechanical feet installed on the aircraft.

[0010] The helmet comprises a shell and a non-trigger air cushion embedded in the shell, and a visual window of transparent material is arranged on the front side of the shell.

[0011] The flight suit comprises a vest, a back airbag mounted on the back of the vest, a chest and abdomen airbag mounted on the front of the vest, each airbag is connected to a gas generator mounted on the vest or the aircraft through a pipeline, and the gas generator is provided with a trigger switch for inflating each airbag;

[0012] When the aircraft is a backpack aircraft, the back airbag is inflated and expanded to form an air cushion filled between the back of the pilot's spine as the central axis and the back plate of the aircraft, and the chest and abdomen airbag is inflated and expanded to form a plurality of spherical or columnar airbags;

[0013] When the aircraft is a straddle aircraft / suspension aircraft with a saddle, the system further comprises a lower abdominal airbag and a hip air cushion embedded in the upper part of the saddle, the lower abdominal airbag and the hip air cushion are connected to the gas generator through a pipeline, the back airbag and the chest and abdomen airbag are inflated and expanded to form a plurality of spherical or columnar airbags, the lower abdominal airbag is inflated and expanded to form a spherical or columnar airbag, and the hip air cushion is inflated and expanded to form an air cushion filled between the pilot's hips and the saddle;

[0014] The mechanical foot comprises a support rod, a rotating rod and a mounting block, the mounting block is connected to the aircraft, one end of the rotating rod is rotatably connected to the mounting block or the aircraft, one end of the support rod is rotatably connected to the other end of the rotating rod, and the other end of the support rod is used as a support foot; when the mechanical foot is in an expanded state, the other end of the rotating rod is lower than one end of the rotating rod, and the other end of the support rod faces downward; when the mechanical foot changes from the expanded state to a folded state, the rotating rod is folded toward the aircraft, and the support rod is folded toward the rotating rod.

[0015] Further, the other end of the support rod is provided with a buffer block in a honeycomb structure

[0016] Further, it further comprises a parachute bag mounted on the aircraft.

[0017] Further, the bottom of the shell is connected with a neck support.

[0018] Further, the mechanical foot is even, and is symmetrically arranged on both sides of the aircraft, preferably 4 or 6.

[0019] Further, the non-trigger air cushion comprises a cap-shaped air cushion for contacting the parietal bone and frontal bone of the pilot's head and a ring-shaped air cushion for contacting the temporal bone and occipital bone of the pilot's head.

[0020] Further, the relative rotation between the rotating rod and the mounting block or the aircraft and the relative rotation between the support rod and the rotating rod are in a passive mode.

[0021] Manner one: the first torsional spring is arranged at the rotating connection between one end of the rotating rod and the mounting block, the second torsional spring is arranged at the rotating connection between one end of the supporting rod and the other end of the rotating rod, when the mechanical foot is in the folding state, the first torsional spring and the second torsional spring are in the compressed state, the mechanical foot is kept in the folding state through the locking member inserted in the mounting block or the aircraft, when the locking member is separated from the mounting block or the aircraft, the mechanical foot changes from the folding state to the unfolding state under the action of the first torsional spring and the second torsional spring, when in the unfolding state, the first torsional spring and the second torsional spring are in the natural state;

[0022] Manner two: the first gas spring is hingedly connected between one end of the rotating rod and the mounting block, the second gas spring is hingedly connected between one end of the supporting rod and the other end of the rotating rod, when the mechanical foot is in the folding state, the first gas spring and the second gas spring are in the compressed state, the mechanical foot is kept in the folding state through the locking member inserted in the mounting block or the aircraft, when the locking member is separated from the mounting block or the aircraft, the mechanical foot changes from the folding state to the unfolding state under the action of the first gas spring and the second gas spring, when in the unfolding state, the first gas spring and the second gas spring are in the natural state.

[0023] Further, the relative rotation between the rotating rod and the mounting block or the aircraft, and the relative rotation between the supporting rod and the rotating rod are in the active mode:

[0024] The rotation of the rotating rod relative to the mounting block or the aircraft is realized through the first driving member, the first driving member is installed on the mounting block or the aircraft, the rotation of the supporting rod relative to the rotating rod is realized through the second driving member, the second driving member is installed on the rotating rod or the supporting rod. Wherein, the first driving member and the second driving member adopt the motor or the air cylinder.

[0025] The beneficial effects of the present application are:

[0026] 1. The landing and lifesaving system of the present application is suitable for non-full-coated single-person aircraft, not only provides multi-directional buffering and protection for the pilot landing and forced landing through the design of the special helmet and flight suit, but also provides support and buffering during landing through the expandable mechanical foot, improves the buffering capacity to strong impact force during forced landing, and improves the safety; and the mechanical foot is in the folding state when not unfolded, which can reduce the occupied volume as much as possible to minimize the influence on the aerodynamic shape envelope of the aircraft;

[0027] 2. The landing and lifesaving system of the present application reduces the difficulty of the pilot forced landing, can not rely on the parachute for forced landing and landing, can shorten the pilot training time, and also solves the dilemma that the parachute cannot be applied during low altitude / ultra-low altitude flight, especially in the case that the parachute cannot be deployed in the low altitude environment with dense buildings, power poles and towers, etc. The system can provide a good landing mode without the weight reduction of the aircraft by abandoning the parachute package;

[0028] 3、The landing and lifesaving system of the present application combines a wearable design, is beneficial to close-to-body protection of the pilot, and basically does not cause additional influence on the attitude control of the aircraft when the airbag is not triggered;

[0029] 4、The mechanical foot of the present application can be realized in a passive mode, has simple structure and is easy to realize, and the expansion realized through the spring / torsional spring mode can further provide buffering capacity when forced landing impact occurs, cooperates with the buffer block in a honeycomb structure to improve the safety of the system and relieve the forced landing impact; the mechanical foot can be realized in an active mode, and when realized in the active mode, the preset program can be cooperated to realize automatic triggering expansion. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 Fig. 1 is a structural schematic diagram of the landing and lifesaving system of the embodiment of the present application.

[0031] Figure 2 Fig. 2 is a structural schematic diagram of the airbag triggering and the mechanical foot in the expanded state of the landing and lifesaving system of the embodiment of the present application.

[0032] Figure 3 Fig. 3 is a three-dimensional structural schematic diagram of the helmet of the embodiment of the present application.

[0033] Figure 4 Fig. 4 is a side structural schematic diagram of the helmet of the embodiment of the present application.

[0034] Figure 5 Fig. 5 is a structural schematic diagram of the flight suit after each airbag triggering when applied to the backpack type aircraft of the embodiment of the present application.

[0035] Figure 6 Fig. 6 is a structural schematic diagram of the flight suit after each airbag triggering when applied to the straddle type aircraft / suspension type aircraft with a straddle of the embodiment of the present application.

[0036] Figure 7 Fig. 7 is an expanded state structural schematic diagram of the mechanical foot when worn in the front of the embodiment of the present application.

[0037] Figure 8 Fig. 8 is a folded state structural schematic diagram of the mechanical foot when worn in the front of the embodiment of the present application.

[0038] Figure 9 Fig. 9 is a folded state structural schematic diagram of the mechanical foot when worn in the back of the embodiment of the present application.

[0039] Figure 10 Fig. 10 is an expanded state structural schematic diagram of the mechanical foot when worn in the back of the embodiment of the present application. DETAILED DESCRIPTION

[0040] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the embodiments of the present application will be described in detail below with reference to the drawings. However, the embodiments described in the present application are only a part of the embodiments of the present application, rather than all the embodiments of the present application.

[0041] The embodiments of the present application provide a landing and lifesaving system suitable for a non-fully-covered single-person aircraft, such as Figure 1 and Figure 2 The system includes a helmet 1 to be worn on the head of a pilot when in use, a flight suit 2 to be worn by the pilot and connected to the aircraft through a safety belt, and a plurality of mechanical feet 3 installed on the aircraft. It should be noted that Figure 1 and Figure 2 The aircraft shown in the above two figures is only an example, and in actual applications, the aircraft referred to in the present embodiment is not limited to the type with wings only.

[0042] Preferably, the mechanical feet 3 are even in number and symmetrically arranged on both sides of the aircraft. Further preferably, the mechanical feet 3 are 4 or 6, such as Figure 1 and Figure 2 as shown in the above two figures.

[0043] Optionally, the system further includes a parachute pack 4 installed on the aircraft, Figure 1 and Figure 2 The above two figures show a schematic view when the parachute pack 4 is not opened. The parachute pack 4 can be selected according to the flight requirements. In low-altitude flight, the parachute pack 4 can generally not be selected to reduce the flight weight; in high-altitude flight, the parachute pack 4 is selected and opened when the relative height difference with the landing site reaches a predetermined range.

[0044] As shown in Figure 3 and Figure 4 , wherein Figure 4 The A area in the above two figures shows a partial cross-sectional view of the internal structure of the helmet 1. The helmet 1 includes a shell 102 and a non-trigger air cushion 101 embedded in the shell 102. The front side of the shell 102 is provided with a visual window 103 made of transparent material, corresponding to the position of the eyes and face of the wearer. The external configuration of the shell 102 is integrally formed to form an aerodynamic shape. The non-trigger air cushion 101 includes a cap-shaped air cushion for contacting the parietal bone and frontal bone of the pilot's head and a ring-shaped air cushion for contacting the temporal bone and occipital bone of the pilot's head. Optionally, the bottom of the shell 102 is also connected with a neck support 104, and a shoulder support can also be configured according to the situation.

[0045] As shown in Figure 1 , Figure 2 , Figure 5 , Figure 6As shown, the flight suit 2 includes a vest 202, a back air bag 201 mounted on the back of the vest 202, and a chest and abdomen air bag 203 mounted on the front of the vest 202. Specifically, the vest 202 can be a skeleton vest or an air bag and air duct support skeleton on the main body of the flight suit 2. Each air bag is connected to a gas generator 200 through a pipeline, the gas generator 200 is mounted on the vest 202 or the aircraft, and the gas generator 200 is provided with a trigger switch for inflating each air bag. The trigger switch here can be a manual trigger switch, or an automatic switch that is automatically triggered according to a preset program during an emergency landing.

[0046] When the aircraft is a backpack aircraft, the main structure of the aircraft basically fits the spine, and the flight suit 2 is fixed by a safety belt, as shown in Figure 5 As shown, the back air bag 201 inflates and expands to form an air cushion filled between the back of the pilot's spine as the central axis and the back plate of the aircraft, and the chest and abdomen air bag 203 inflates and expands to form a plurality of spherical or columnar air bags.

[0047] When the aircraft is a straddle-type aircraft / suspension aircraft with a straddle, the pilot adopts a straddle driving mode, and the hips are non-fixedly connected to the straddle, as shown in Figure 6 As shown, the system further includes a lower abdominal air bag 204 and a hip air cushion 205 embedded on the upper part of the straddle, the lower abdominal air bag 204 and the hip air cushion 205 are connected to the gas generator 200 through a pipeline, the back air bag 201 and the chest and abdomen air bag 203 inflate and expand to form a plurality of spherical or columnar air bags, the lower abdominal air bag 204 inflates and expands to form a spherical or columnar air bag, and the hip air cushion 205 inflates and expands to form an air cushion filled between the hips of the pilot and the straddle.

[0048] During normal flight, the mechanical foot 3 is retracted, as shown in Figure 1 During normal landing or emergency landing, the mechanical foot 3 is expanded, as shown in Figure 2

[0049] Specifically, as shown in Figure 7 - Figure 10 The mechanical foot 3 includes a support rod 301, a rotating rod 302, and a mounting block 303, the mounting block 303 is connected to the aircraft, one end of the rotating rod 302 is rotatably connected to the mounting block 303 or the aircraft, one end of the support rod 301 is rotatably connected to the other end of the rotating rod 302, and the other end of the support rod 301 is used as a support foot. Preferably, a buffer block 304 in a honeycomb structure is mounted on the other end of the support rod 301, and the material can be rubber material that can compress and absorb impact energy.

[0050] When the mechanical foot 3 is in the expanded state, the other end of the rotating rod 302 is lower than one end of the rotating rod 302, and the other end of the support rod 301 faces downward, as shown in Figure 7 and Figure 10 ​As shown; when the mechanical foot 3 is transformed from the unfolded state to the folded state, the rotating rod 302 is folded towards the aircraft, and the supporting rod 301 is folded towards the rotating rod 302, as shown in Figure 8 and Figure 9 .

[0051] Specifically, the mechanical foot 3 has two installation modes, i.e. the normal mode and the reverse mode. As shown in Figure 7 and Figure 8 , which is an example of the normal mode, when the mechanical foot 3 is in the folded state as shown in Figure 8 , the rotating rod 302 and the supporting rod 301 are folded, and the other end of the supporting rod 301 is upward; as shown in Figure 9 and Figure 10 , which is an example of the reverse mode, when the mechanical foot 3 is in the folded state as shown in Figure 9 , the rotating rod 302 and the supporting rod 301 are folded, and the other end of the supporting rod 301 is downward.

[0052] Specifically, the mechanical foot 3 can be transformed from the folded state to the unfolded state in two ways, i.e. the passive way and the active way.

[0053] The passive way can be realized by spring / air spring, torsional spring, etc. When folded, the folding state is maintained / fixed by the lock 300 which is convenient to open or disassemble, as shown in Figure 8 , when unfolded, the lock 300 is disassembled or pulled off to release the fixed state, so as to realize the unfolding by the self-resetting characteristics of the spring / air spring, torsional spring, etc. When unfolded, as shown in Figure 7 and Figure 10 .

[0054] One of the passive ways, as shown in Figure 7 , a first torsional spring is arranged at the rotating connection between one end of the rotating rod 302 and the mounting block 303, and a second torsional spring is arranged at the rotating connection between the other end of the rotating rod 302 and one end of the supporting rod 301. Specifically, the first torsional spring can be arranged inside the mounting block 303, one end of which is connected to the mounting block 303, and the other end of which is connected to a first rotating shaft, which is fixedly connected to one end of the rotating rod 302 and rotatably connected to the mounting block 303. Similarly, one end of the supporting rod 301 is rotatably connected to the other end of the rotating rod 302 through a second rotating shaft fixedly connected to one end of the supporting rod 301, and a second torsional spring is arranged at the second rotating shaft, one end of which is connected to the rotating rod 302, and the other end of which is connected to the second rotating shaft. Specifically, the second torsional spring can be arranged in the mounting shell arranged at the end of the supporting rod 301. When the mechanical foot 3 is in the folded state, the first torsional spring and the second torsional spring are in the compressed state, and the mechanical foot 3 is maintained in the folded state by the lock 300 arranged in the mounting block 303 or the aircraft, as shown in Figure 8When the locking member 300 is detached from the mounting block 303 or the aircraft, the mechanical foot 3 changes from the folded state to the unfolded state under the action of the first torsional spring and the second torsional spring, as shown in Figure 7 When the locking member 300 is detached from the mounting block 303 or the aircraft, the mechanical foot 3 changes from the folded state to the unfolded state under the action of the first torsional spring and the second torsional spring, as shown in

[0055] Another passive mode is as follows: Figure 8 - Figure 10 As shown in the figure, the first gas spring 305 is hingedly connected between one end of the rotating rod 302 and the mounting block 303, and the second gas spring 306 is hingedly connected between one end of the supporting rod 301 and the other end of the rotating rod 302. When the mechanical foot 3 is in the folded state, as shown in Figure 8 , Figure 9 As shown in the figure, the first gas spring 305 and the second gas spring 306 are in a compressed state; as shown in the figure, the mechanical foot 3 is kept in the folded state by the locking member 300 inserted in the mounting block 303 or the aircraft; when the locking member 300 is detached from the mounting block 303 or the aircraft, the mechanical foot 3 changes from the folded state to the unfolded state under the action of the first gas spring 305 and the second gas spring 306, and is in the unfolded state, as shown in Figure 8 As shown in the figure, the first gas spring 305 and the second gas spring 306 are in a natural state. Specifically, according to the requirements of the rotation angle of the supporting rod 301 in the normal or reverse installation, the positions of the first gas spring 305 and the second gas spring 306 and the positions of the hinged points connected thereto can be flexibly configured, so as to adapt to the requirements of the rotation angle and avoid the rotation interference caused by the supporting rod 301 and the rotating rod 302. As shown in the figure, Figure 10 As shown in the figure, the first gas spring 305 and the second gas spring 306 are in a natural state. Specifically, according to the requirements of the rotation angle of the supporting rod 301 in the normal or reverse installation, the positions of the first gas spring 305 and the second gas spring 306 and the positions of the hinged points connected thereto can be flexibly configured, so as to adapt to the requirements of the rotation angle and avoid the rotation interference caused by the supporting rod 301 and the rotating rod 302. As shown in the figure, Figure 10 As shown in the figure, the second gas spring 306 and the hinged point of the supporting rod 301 can be arranged on an extension rod 307 mounted on the supporting rod 301, so as to adapt to the requirements of the rotation angle and avoid interference by adjusting the length of the extension rod 307. The extension rod 307 is selected to have a lockable length.

[0056] The above passive mode can save the configuration of the power source and simplify the system structure, and can also reduce the mass of the aircraft, which is beneficial to better control of the flight attitude. When landing or forced landing is required, the pilot can pull out the locking member 300. Specifically, the locking member 300 can be a detachable insertion connection sleeve lock / sleeve ring that can simultaneously cover the supporting rod 301 and the rotating rod 302 and the mounting block 303 or the aircraft.

[0057] The active mode can be configured with a power source / drive source for implementation. In specific operation, the aircraft can press the configured switch or the switch can be automatically triggered by a preset program to change from the folded state to the unfolded state.

[0058] One of the active ways, the rotation of the rotating rod 302 relative to the mounting block 303 or the aircraft is realized by the first driving member, which is mounted on the mounting block 303 or the aircraft. Specifically, the first driving member can be a first motor mounted on the mounting block 303 or the aircraft, and the output shaft of the first motor is connected with the first rotating shaft mounted on the rotating rod 302. The rotating rod 302 is rotatably connected with the mounting block 303 or the aircraft through the first rotating shaft. Similarly,

[0059] The rotation of the supporting rod 301 relative to the rotating rod 302 is realized by the second driving member, which is mounted on the rotating rod 302 or the supporting rod 301. Specifically, the second driving member can be a second motor mounted on the rotating rod 302, and the output shaft of the second motor is connected with the second rotating shaft mounted on the supporting rod 301. The supporting rod 301 is rotatably connected with the rotating rod 302 through the second rotating shaft. In this embodiment, the first motor and the second motor can be replaced by the first rotary cylinder and the second rotary cylinder, respectively.

[0060] On this basis, in order to improve the stability of the folded state and the unfolded state, a worm and a worm wheel structure is added. The worm is connected to the output shaft of the first motor / second motor, and the worm wheel is matched with the worm and coaxially connected to the first rotating shaft / second rotating shaft.

[0061] In another active way, the first gas spring 305 and the second gas spring 306 in the passive way described above can be replaced by the first linear mechanism and the second linear mechanism, respectively. The state change is realized by the extension and retraction of the linear cylinder. The first linear mechanism and the second linear mechanism can be a cylinder, a hydraulic cylinder, a lead screw / electric screw.

[0062] The above is only the preferred embodiment of the present application, and does not mean the only or limit the present application. Those skilled in the art should understand that various changes or equivalent replacements of the present application without departing from the scope of the present application, all belong to the scope of protection of the present application.

Claims

1. A landing and rescue system for a non-fully-enclosed single-person aircraft, characterized in that, The system comprises a helmet (1) worn on the head of a pilot, a flight suit (2) connected to the aircraft through a safety belt and worn by the pilot, and a plurality of mechanical feet (3) installed on the aircraft; The helmet (1) comprises a shell (102) and a non-trigger air cushion (101) embedded in the shell (102), and a visual window (103) made of transparent material is arranged on the front side of the shell (102); The flight suit (2) comprises a vest (202), a back air bag (201) installed on the back of the vest (202), and a chest and abdomen air bag (203) installed on the front of the vest (202), each air bag is connected to the gas generator (200) installed on the vest (202) or the aircraft through a pipeline, and a trigger switch for inflating each air bag is arranged on the gas generator (200); When the aircraft is a backpack aircraft, the back air bag (201) is inflated and expanded to form an air cushion filled between the back of the pilot's spine as the central axis and the back plate of the aircraft, and the chest and abdomen air bag (203) is inflated and expanded to form a plurality of spherical or columnar air bags; When the aircraft is a straddle-type aircraft / hanging aircraft with a saddle, the system further comprises a lower abdominal air bag (204) and a hip air cushion (205) embedded in the upper part of the saddle, the lower abdominal air bag (204) and the hip air cushion (205) are connected to the gas generator (200) through a pipeline, the back air bag (201) and the chest and abdomen air bag (203) are inflated and expanded to form a plurality of spherical or columnar air bags, the lower abdominal air bag (204) is inflated and expanded to form a spherical or columnar air bag, and the hip air cushion (205) is inflated and expanded to form an air cushion filled between the hips of the pilot and the saddle; The mechanical foot (3) comprises a support rod (301), a rotating rod (302), and a mounting block (303), the mounting block (303) is connected to the aircraft, one end of the rotating rod (302) is rotatably connected to the mounting block (303) or the aircraft, one end of the support rod (301) is rotatably connected to the other end of the rotating rod (302), and the other end of the support rod (301) is used as a support foot; when the mechanical foot (3) is in an expanded state, the other end of the rotating rod (302) is lower than one end of the rotating rod (302), and the other end of the support rod (301) faces downward; when the mechanical foot (3) changes from the expanded state to a folded state, the rotating rod (302) is folded towards the aircraft, and the support rod (301) is folded towards the rotating rod (302).

2. The landing and rescue system for a non-fully-enclosed single-person aircraft of claim 1, wherein, A parachute bag (4) is installed on the aircraft.

3. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, A neck support (104) is connected to the bottom of the shell (102).

4. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The mechanical foot (3) is even and symmetrically arranged on both sides of the aircraft.

5. The landing and rescue system for a non-fully-enclosed single-person aircraft of claim 4, wherein, The mechanical foot (3) is four or six.

6. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The non-trigger air cushion (101) comprises a cap-shaped air cushion for contacting the parietal bone and frontal bone of the pilot's head, and a ring-shaped air cushion for contacting the temporal bone and occipital bone of the pilot's head.

7. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The first torsion spring is arranged at the rotating connection between one end of the rotating rod (302) and the mounting block (303), and the second torsion spring is arranged at the rotating connection between one end of the supporting rod (301) and the other end of the rotating rod (302); when the mechanical foot (3) is in the folded state, the first torsion spring and the second torsion spring are in the compressed state, the mechanical foot (3) is kept in the folded state by the locking member (300) inserted into the mounting block (303) or the aircraft, when the locking member (300) is separated from the mounting block (303) or the aircraft, the mechanical foot (3) changes from the folded state to the unfolded state under the action of the first torsion spring and the second torsion spring, and when in the unfolded state, the first torsion spring and the second torsion spring are in the natural state.

8. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The first gas spring (305) is hingedly connected between one end of the rotating rod (302) and the mounting block (303), and the second gas spring (306) is hingedly connected between one end of the supporting rod (301) and the other end of the rotating rod (302); when the mechanical foot (3) is in the folded state, the first gas spring (305) and the second gas spring (306) are in the compressed state, the mechanical foot (3) is kept in the folded state by the locking member (300) inserted into the mounting block (303) or the aircraft, when the locking member (300) is separated from the mounting block (303) or the aircraft, the mechanical foot (3) changes from the folded state to the unfolded state under the action of the first gas spring (305) and the second gas spring (306), and when in the unfolded state, the first gas spring (305) and the second gas spring (306) are in the natural state.

9. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The rotation of the rotating rod (302) relative to the mounting block (303) or the aircraft is realized by the first driving member, the first driving member is installed on the mounting block (303) or the aircraft, and the rotation of the supporting rod (301) relative to the rotating rod (302) is realized by the second driving member, the second driving member is installed on the rotating rod (302) or the supporting rod (301).

10. The landing and rescue system for a non-fully-enclosed single occupant aircraft of claim 1, wherein, The other end of the supporting rod (301) is provided with a buffer block (304) in a honeycomb structure.

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