A mother-daughter type split-type flight-assisted aircraft

Abstract

This invention discloses a mother-daughter type split-type flight-assisted aircraft, relating to the field of aircraft technology. It includes a large-wingspan UAV, on which a wireless signaler is fixed, and a fairing is fixed to the nose of the UAV. A mounting base is provided on the outer side of the fairing and is fixed to the aircraft. The fairing is respectively provided with a transmission component and a locking component for locking the mounting base. The transmission component includes a servo motor embedded in the fairing, and the locking component includes a circuit breaker fixed to the servo motor. The inner side of the fairing is respectively provided with a pressurization component and a pneumatic thrust component for boosting the mounting base. The pressurization component includes a second electric push rod rotating within the fairing. This invention, based on rapid locking and unlocking conditions using both electromagnetic and mechanical means, achieves a reusable, low-cost boosting effect for small and medium-sized aircraft during short-distance takeoff.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a mother-daughter type split-type flight-assisted aircraft. Background Technology

[0002] Small and medium-sized passenger aircraft are widely used in regional passenger transport, air tourism, emergency commuting and other fields. However, due to limitations in power layout and fuselage structure, some models have insufficient short takeoff performance. When performing missions at small airports or temporary takeoff and landing points, they often need to sacrifice payload or rely on additional booster equipment.

[0003] To force small and medium-sized aircraft to take off short distances, boosters need to be added to the rear of these aircraft. However, among the existing booster takeoff methods, rocket booster technology is a one-time use technology with high costs and limited applicability. At the same time, rocket boosters also have drawbacks such as long cycles and high costs in power modification, and may also disrupt the original power balance of the aircraft, making it a losing proposition. Summary of the Invention

[0004] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0005] In view of the problems existing in the above and / or existing mother-daughter type split-type flight-assisted aircraft, the present invention is proposed.

[0006] Therefore, the problem to be solved by this invention is how to achieve a reusable, low-cost boost effect for small and medium-sized aircraft during short-distance takeoff under conditions of rapid locking and unlocking based on both electromagnetic and mechanical means.

[0007] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a mother-daughter type split-type flight-assisted aircraft, including a large-wingspan UAV that is aided by a rear propeller and a side propeller, and the large-wingspan UAV is monitored by a wireless signal device fixed to its tail.

[0008] The fairing is equipped with a transmission component and a locking component. The transmission component includes a servo motor embedded in the fairing, which is used to mechanically lock the drive source.

[0009] The locking assembly includes a circuit breaker mounted on the servo motor for electromagnetic locking of the control source.

[0010] The aircraft is fixed on the mounting base.

[0011] The locking assembly applies both mechanical and electromagnetic locking actions between the large wingspan UAV and the aircraft.

[0012] The inner side of the fairing is provided with a pressurization assembly and a pneumatic propulsion assembly for mounting the booster. The pressurization assembly includes a pressurization chamber opened inside the fairing and a pressurization piston that slides to pressurize and perform work.

[0013] The air propulsion assembly includes a pressurization tank fixed on the fairing, which is pressurized by a pressurization piston to perform work and supply pressurized air to the pressurization tank.

[0014] The pressurization tank serves as the pressurization air source, applying impact air thrust to the aircraft mounted on the mounting base.

[0015] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, the transmission assembly further includes a main bevel gear sleeved on the output shaft of the servo motor, and a first slave bevel gear is provided on the outer side of the main bevel gear.

[0016] The first electric push rod, which rotates with the fairing, is fixed to the inner side of the first bevel gear.

[0017] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, wherein: a first auxiliary gear is sleeved on the first electric push rod, and a first differential gear is meshed around the first auxiliary gear. A short threaded rod that rotates with the fairing is fixed to the outer side of the first differential gear.

[0018] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, the locking assembly further includes an electromagnet fixed to the outside of the fairing, and the circuit breaker is electrically connected to the electromagnet. The electromagnet has a fixed magnet on its outer side that is fixed to the mounting base.

[0019] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, the mounting base is provided with locking grooves on all four sides, and the threaded short rod is threadedly connected with a threaded sleeve. The outer side of the threaded sleeve is fixed with a locking arm that slides through the fairing, and the inner side of the locking arm is fixed with a locking element that engages with the locking groove.

[0020] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, the pressurization component further includes a second electric push rod that rotates within the fairing, and the second electric push rod is fixed to a second driven bevel gear, and a second auxiliary gear is sleeved on the second electric push rod.

[0021] Furthermore, the outer side of the second auxiliary gear is engaged with the second differential gear.

[0022] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, wherein: a cam is fixed on the outer side of the second differential gear via a concentric shaft, and a connecting rod hinged to the cam and hinged to the booster piston.

[0023] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, wherein: the air propulsion assembly further includes a pressure boosting valve connected to the outer end of the pressure boosting chamber, and a pressure sensor is provided on the pressure boosting valve; The outer end of the pressure boosting valve is connected to a pressure boosting pipe, and the pressure boosting pipe is connected to the pressure boosting tank.

[0024] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, wherein: the outer end of the pressurization tank is connected to a pressure relief valve in one direction, and the outer end of the pressure relief valve is connected to a jet nozzle; A reinforcing arm is fixed on the mounting base, and an air thruster that matches the jet nozzle is fixed on the inner side of the reinforcing arm.

[0025] As a preferred embodiment of the mother-daughter type split-type flight-assisted aircraft of the present invention, wherein: the wireless signal device is respectively embedded with a wireless transceiver, an altitude sensor, a speed sensor, an attitude sensor and a GPS positioning module; Furthermore, a cushioning pad is placed between the mounting base and the aircraft.

[0026] The beneficial effects of this invention are as follows: Through the transmission and locking components, based on electromagnetic and mechanical dual rapid locking and unlocking, and under sensor triggering conditions, a multi-engine battery-powered UAV is used for assisted takeoff, which is compatible with various small and medium-sized aircraft, improves the short-distance takeoff performance of aircraft, realizes the reuse of UAVs, and reduces the operating costs of general aviation. Through the pressurization and air thrust components, the UAV performs reciprocating pressurization work during the boost. Under the action of pressurization pressure, high-pressure gas impact is used to achieve an impact-type boost effect on various small and medium-sized aircraft after unlocking, forcing various small and medium-sized aircraft to have more confidence in short-distance takeoff and making takeoff more effective. Attached Figure Description

[0027] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a front view of the overall structure of a mother-daughter type split-type flight-assisted aircraft.

[0029] Figure 2 This is a partial top view of the structure of a mother-daughter type split-type flight-assisted aircraft.

[0030] Figure 3 A bottom view of a partial structure of a mother-daughter type split-type flight-assisted aircraft.

[0031] Figure 4 An exploded rear view of the fairing and mounting base of a mother-daughter type split-type flight aid aircraft.

[0032] Figure 5 Exploded front view of the fairing and mounting base of the mother-daughter type split-type flight aid aircraft.

[0033] Figure 6 A partial cross-sectional view of the fairing of a mother-daughter type split-type flight-assisted aircraft.

[0034] Figure 7 For mother-daughter type split-type flight-assisted aircraft Figure 6 Enlarged view of the structure at point A in the middle.

[0035] Figure 8 A partial exploded view of the transmission, locking, and pressurization components of a mother-daughter type split-type flight-assisted aircraft.

[0036] Figure 9 Exploded view of the propulsion assembly and mounting base of a mother-daughter type split-type flight-assisted aircraft.

[0037] In the diagram: 1. Large wingspan UAV; 2. Wireless signal receiver; 3. Fairing; 4. Mounting base; 51. Servo motor; 52. Main bevel gear; 53. First driven bevel gear; 54. First electric push rod; 55. First auxiliary gear; 56. First differential gear; 57. Threaded short rod; 61. Circuit breaker; 62. Electromagnet; 63. Fixed magnet; 64. Locking groove; 65. Threaded sleeve; 66. Locking arm; 67. Locking element; 7 1. Second bevel gear; 72. Second electric push rod; 73. Second auxiliary gear; 74. Second differential gear; 75. Cam; 76. Connecting rod; 77. Pressure boosting piston; 81. Pressure boosting valve; 82. Pressure boosting pipe; 83. Pressure boosting tank; 84. Pressure relief valve; 85. Jet nozzle; 86. Reinforcing arm; 87. Air thruster; 9. Pressure boosting chamber; 10. Buffer pad; 11. Aircraft; 12. Rear propeller; 13. Side propeller. Detailed Implementation

[0038] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0039] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0040] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0041] Example 1, referring to Figures 1-9 This is the first embodiment of the present invention. This embodiment provides a mother-daughter type split-type flight-assisted aircraft, including a large-wingspan UAV 1 assisted by a rear propeller 12 and a side propeller 13. The rear propeller 12 and the side propeller 13 are designed with electric motor drive to provide sufficient boost to the large-wingspan UAV 1, avoid the phenomenon of a small horse pulling a large cart, and facilitate the effective boost of small and medium-sized aircraft.

[0042] In the boosted combination state of the large wingspan UAV 1 and the aircraft 11, the large wingspan UAV 1 provides the main lift and thrust, carrying the aircraft 11 to complete the take-off maneuver. During this stage, the aircraft 11 is in the engine state and does not need to consume the energy of a traditional aircraft during take-off and climb. After separation, the large wingspan UAV 1 executes the autonomous return and recovery procedure, and the aircraft 11 switches from the engine state to start its own power system, allowing the pilot on the aircraft 11 to independently carry out the flight mission.

[0043] A wireless signaler 2 is fixed on the large wingspan UAV 1. The wireless signaler 2 is equipped with a wireless transceiver, an altitude sensor, a speed sensor, an attitude sensor, and a GPS positioning module. The wireless signaler 2 transmits and receives tower command information. The altitude, speed, and attitude sensors monitor the flight altitude, speed, and attitude of the large wingspan UAV 1 and the aircraft 11 in real time to ensure that the large wingspan UAV 1 executes the correct boost procedure for the aircraft 11.

[0044] The inertial navigation module, which works in conjunction with the GPS positioning module, is installed in the wireless signal unit 2. This enables the large-wingspan UAV 1 to receive tower commands after separation and return autonomously. This achieves high-precision positioning and autonomous recovery of the large-wingspan UAV 1, reducing the repeated boost costs of small and medium-sized aircraft.

[0045] Furthermore, a fairing 3 is fixed at the nose of the large wingspan UAV 1, and a mounting base 4 is provided on the outer side of the fairing 3. The mounting base 4 is fixed to the aircraft 11, and a buffer pad 10 is provided between the mounting base 4 and the aircraft 11. Through the buffer pad 10, the aircraft 11 is provided with inertial protection during the boosting of the large wingspan UAV 1, so as to avoid dents and damage to the stress area of ​​the aircraft 11. The buffer pad 10 is made of polyurethane material with a thickness of 20mm, which can effectively absorb the load impact during takeoff and separation.

[0046] Specifically, when the large-wingspan UAV 1 and aircraft 11 combine to reach the preset altitude, speed, and attitude conditions set by the altitude sensor, speed sensor, and attitude sensor, the control tower and sensor module send an unlocking command to the locking component to separate the large-wingspan UAV 1 and aircraft 11. The control tower sends a remote unlocking command via a 4G / 5G network. The onboard sensors on the large-wingspan UAV 1 and aircraft 11 can monitor the preset altitude of the combination as 1200m, the preset speed as 160km / h, and the preset pitch angle as 6°. When the parameters meet the requirements, the locking component automatically triggers unlocking. The two methods can be executed independently.

[0047] Before separation, the large wingspan UAV 1 fine-tunes its attitude through the flight control system, so that the aircraft 11 and the large wingspan UAV 1 form an angle difference of 5-15° and a speed difference of 0.5-1m / s, so as to avoid airflow interference and collision between the two after separation. At the same time, before separation, the aircraft 11 is controlled by the pilot to adjust to the flight attitude and engine output power of the normal climb phase.

[0048] After the large-wingspan UAV 1 and the aircraft 11 separate, the large-wingspan UAV 1 immediately performs a descent and separation maneuver, and initiates an autonomous return program to return to the preset recovery point; the aircraft 11 simultaneously makes minor adjustments to its heading and continues to climb, leaving the wake turbulence area of ​​the large-wingspan UAV 1, and continues to use its own power and flight control system to perform the preset flight mission.

[0049] Example 2, refer to Figures 1-9 This is the second embodiment of the present invention, which is based on the previous embodiment.

[0050] Specifically, the fairing 3 is provided with a transmission assembly and a locking assembly for locking the mounting base 4. The transmission assembly includes a servo motor 51 embedded in the fairing 3 and a main bevel gear 52 sleeved on the output shaft of the servo motor 51. A first driven bevel gear 53 is provided on the outer side of the main bevel gear 52. A first electric push rod 54 that rotates with the fairing 3 is fixed on the inner side of the first driven bevel gear 53. The meshing stroke between the main bevel gear 52 and the first driven bevel gear 53 is adjusted to the correct position by the first electric push rod 54 to perform the mechanical locking action.

[0051] The first electric push rod 54 is fitted with a first auxiliary gear 55, and the first auxiliary gear 55 is meshed with a first differential gear 56 on all four sides. A threaded short rod 57 that rotates with the fairing 3 is fixed on the outside of the first differential gear 56.

[0052] In use: First, control the first electric push rod 54 to open, and drive the first driven bevel gear 53 to move inward and engage with the main bevel gear 52. Then, control the servo motor 51 to open, and drive the first auxiliary gear 55 on it to rotate through the engaged main bevel gear 52 and the first driven bevel gear 53. Then, the first auxiliary gear 55 drives the four sets of first differential gears 56 and the threaded short rod 57 to rotate synchronously in the forward direction, completing the transmission state before mechanical locking.

[0053] Specifically, locking grooves 64 are provided around the mounting base 4, and a threaded sleeve 65 is threadedly connected to the threaded short rod 57. A locking arm 66 that slides through the fairing 3 is fixed on the outer side of the threaded sleeve 65, and a locking member 67 that engages with the locking groove 64 is fixed on the inner side of the locking arm 66.

[0054] In use: The four threaded short rods 57 that rotate synchronously in the forward direction drive the locking parts 67 on the four locking arms 66 through the threaded sleeves 65 on them, and synchronously lock into the locking grooves 64 on the mounting base 4, completing the rapid mechanical locking action of the large wingspan UAV 1 and the aircraft 11, forming a combination, with the large wingspan UAV 1 carrying the aircraft 11 for flight assistance.

[0055] When the airborne sensor group reaches the preset altitude, speed and attitude angle values, or receives the tower unlocking command, the servo motor 51 is quickly reversed, and the four sets of locking parts 67 disengage from the locking grooves 64 on the mounting base 4, completing the rapid mechanical unlocking action of the large wingspan UAV 1 and the aircraft 11.

[0056] Specifically, the locking assembly includes a circuit breaker 61 fixed on the servo motor 51, and an electromagnet 62 fixed on the outside of the rectifier 3. The circuit breaker 61 is electrically connected to the electromagnet 62, and a fixed magnet 63 fixed to the mounting base 4 is provided on the outside of the electromagnet 62.

[0057] In use: The circuit breaker 61 controls the electromagnet 62 to energize the fixed magnet 63, so that the energized electromagnet 62 generates a strong electromagnetic attraction force on the fixed magnet 63. Then, through the electromagnetic attraction state of the electromagnet 62 and the fixed magnet 63, the fairing 3 and the mounting base 4 are electromagnetically locked. Then, the large wingspan UAV 1 and the aircraft 11 are quickly electromagnetically locked, forming a combination. After the mechanical lock and electromagnetic lock are completed, the large wingspan UAV 1 carries the aircraft 11 and executes the boost procedure.

[0058] When the airborne sensor group reaches the preset altitude, speed, and attitude angle values, or receives the tower unlock command, the circuit breaker 61 controls the electromagnet 62 to cut off the power to the stationary magnet 63, so that the electromagnet 62 loses its strong electromagnetic attraction to the stationary magnet 63. Then, through the unlocking action of the electromagnet 62 and the stationary magnet 63, the fairing 3 and the mounting base 4, as well as the large wingspan UAV 1 and the aircraft 11, are quickly unlocked electromagnetically. When both the mechanical lock and the electromagnetic lock have completed the dual unlocking state, the servo motor 51 and the first electric push rod 54 are turned off and reset to the initial state. The large wingspan UAV 1 returns autonomously to the base for charging, while the aircraft 11 performs a climb flight mission.

[0059] Example 3, referring to Figures 1-9 This is the third embodiment of the present invention, which is based on the first two embodiments.

[0060] Specifically, the inner side of the fairing 3 is provided with a pressurization assembly and a pneumatic propulsion assembly for mounting the base 4. The pressurization assembly includes a second electric push rod 72 that rotates inside the fairing 3, and a second driven bevel gear 71 located outside the main bevel gear 52. The second electric push rod 72 is fixed to the second driven bevel gear 71. The meshing stroke between the main bevel gear 52 and the second driven bevel gear 71 is adjusted to the correct position through the second electric push rod 72.

[0061] The second electric push rod 72 is fitted with a second auxiliary gear 73, and the outer side of the second auxiliary gear 73 is meshed with a second differential gear 74.

[0062] In use: First, control the second electric push rod 72 to open, and drive the second bevel gear 71 to move inward and engage with the main bevel gear 52. Then, control the servo motor 51 to open, and drive the second auxiliary gear 73 on it to rotate through the engaged main bevel gear 52 and the second bevel gear 71. Then, the second auxiliary gear 73 drives the three sets of second differential gears 74 to rotate synchronously.

[0063] The fairing 3 has a booster chamber 9 inside, and a cam 75 is fixed to the outside of the second differential gear 74 via a concentric shaft. A connecting rod 76 is hinged to the cam 75, and a booster piston 77 that slides with the booster chamber 9 is hinged to the connecting rod 76.

[0064] In use: The three sets of second differential gears 74 in the rotating state drive the three cams 75 to rotate synchronously through the concentric shaft. The three cams 75 drive the booster pistons 77 on the connecting rod 76 to perform reciprocating boosting work in the three sets of booster chambers 9, so as to prepare for booster air propulsion before the assembly is separated.

[0065] Specifically, the air propulsion assembly includes a pressurization tank 83 fixed to the fairing 3 by a fastener, and a pressurization valve 81 connected to the outer end of the pressurization chamber 9. The pressurization valve 81 is equipped with a pressure sensor, and the outer end of the pressurization valve 81 is connected to a pressurization pipe 82, which is connected to the pressurization tank 83.

[0066] In use: The high-speed work generated in the three pressurization chambers 9 generates pressurization pressure. The three open pressurization valves 81 are further pressurized by the three pressurization pipes 82 and then supplied to the three pressurization tanks 83 for pressurization and storage. After the assembly completes the double unlocking separation procedure, it is used as preparation for pressurized gas injection. When the pressure sensors on the three pressurization pipes 82 detect that the pressurization pressure in the three pressurization tanks 83 has reached the preset maximum threshold, they control the servo motor 51 and the second electric push rod 72 to close, reset to the initial state, and stop pressurization.

[0067] The outer end of the pressurization tank 83 is connected to a pressure relief valve 84, and the outer end of the pressure relief valve 84 is connected to a jet nozzle 85. A reinforcing arm 86 is fixed on the mounting base 4, and an air thruster 87 that matches the jet nozzle 85 is fixed on the inner side of the reinforcing arm 86.

[0068] In use: The pressurized gas stored in the three pressurization tanks 83 is pressurized and injected into the three air thrusters 87 through the three open pressure relief valves 84 and the three jet nozzles 85. Under the action of the pressurized impact force, the aircraft 11 is given a final impact boost through the double-unlocked mounting base 4. Before the air thrust, the aircraft 11 is adjusted and prepared to make the aircraft 11 fly with more confidence and more stable and effective flight.

[0069] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A mother-daughter type split-type flight-assisted aircraft, characterized in that: include A large-wingspan unmanned aerial vehicle (1) is aided by a rear propeller (12) and a side propeller (13), and the large-wingspan unmanned aerial vehicle (1) is sensed and monitored by a wireless signal device (2) fixed to its tail. The fairing (3) is provided with a transmission component and a locking component. The transmission component includes a servo motor (51) embedded in the fairing (3) to mechanically lock the drive source. The locking assembly includes a circuit breaker (61) fixed to the servo motor (51) for electromagnetically locking the control source; The aircraft (11) is fixed on the mounting base (4); A mechanical and electromagnetic dual locking action is applied between the large wingspan UAV (1) and the aircraft (11) by a locking assembly; The inner side of the fairing (3) is provided with a pressurization assembly and a pneumatic propulsion assembly for the mounting base (4) to boost the power. The pressurization assembly includes a pressurization chamber (9) opened in the fairing (3) and a pressurization piston (77) that slides thereon for pressurization to do work. The air propulsion assembly includes a pressurization tank (83) fixed on the fairing (3), which is pressurized by a pressurization piston (77) to do work and provide pressurized air supply to the pressurization tank (83); The pressurization tank (83) serves as the pressurization gas source, applying impact gas propulsion to the aircraft (11) on the mounting base (4).

2. The mother-daughter type split-type flight-assisted aircraft as described in claim 1, characterized in that: The transmission assembly also includes a main bevel gear (52) sleeved on the output shaft of the servo motor (51), and a first slave bevel gear (53) is provided on the outer side of the main bevel gear (52). The first electric push rod (54) that rotates with the fairing (3) is fixed to the inner side of the first bevel gear (53).

3. The mother-daughter type split-type flight-assisted aircraft as described in claim 2, characterized in that: The first electric push rod (54) is fitted with a first auxiliary gear (55), and the first auxiliary gear (55) is meshed with a first differential gear (56) on all four sides. The outer side of the first differential gear (56) is fixed with a threaded short rod (57) that rotates with the fairing (3).

4. The mother-daughter type split-type flight-assisted aircraft as described in claim 1 or 3, characterized in that: The locking assembly also includes an electromagnet (62) fixed to the outside of the fairing (3), and the circuit breaker (61) is electrically connected to the electromagnet (62); The electromagnet (62) is provided with a fixed magnet (63) fixed to the mounting base (4) on its outer side.

5. The mother-daughter type split-type flight-assisted aircraft as described in claim 1 or 3, characterized in that: Locking grooves (64) are provided around the mounting base (4), and a threaded sleeve (65) is threadedly connected to the threaded short rod (57). The outer side of the threaded sleeve (65) is fixed with a locking arm (66) that slides through the fairing (3), and the inner side of the locking arm (66) is fixed with a locking member (67) that engages with the locking groove (64).

6. The mother-daughter type split-type flight-assisted aircraft as described in claim 1, characterized in that: The pressurization assembly also includes a second electric push rod (72) that rotates inside the fairing (3), and a second bevel gear (71) is fixed on the inner side of the second electric push rod (72), and a second auxiliary gear (73) is sleeved on the second electric push rod (72). Furthermore, the outer side of the second auxiliary gear (73) is engaged with the second differential gear (74).

7. The mother-daughter type split-type flight-assisted aircraft as described in claim 6, characterized in that: A cam (75) is fixed to the outer side of the second differential gear (74) via a concentric shaft, and a connecting rod (76) hinged to the cam (75) and hinged to the booster piston (77).

8. The mother-daughter type split-type flight-assisted aircraft as described in claim 1, characterized in that: The pneumatic propulsion assembly also includes a pressure boosting valve (81) connected to the outer end of the pressure boosting chamber (9), and a pressure sensor is provided on the pressure boosting valve (81); The outer end of the pressure boosting valve (81) is connected to a pressure boosting pipe (82), and the pressure boosting pipe (82) is connected to the pressure boosting tank (83).

9. The mother-daughter type split-type flight-assisted aircraft as described in claim 8, characterized in that: The outer end of the pressurizing tank (83) is connected to a pressure relief valve (84) in one direction, and the outer end of the pressure relief valve (84) is connected to a jet nozzle (85). A reinforcing arm (86) is fixed on the mounting base (4), and an air thruster (87) that matches the jet nozzle (85) is fixed on the inner side of the reinforcing arm (86).

10. The mother-daughter type split-type flight-assisted aircraft as described in claim 1, characterized in that: The wireless transceiver (2) is respectively embedded with a wireless transceiver, a height sensor, a speed sensor, an attitude sensor and a GPS positioning module; Furthermore, a buffer pad (10) is provided between the mounting base (4) and the aircraft (11).

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