CN116639255A - Aircraft transmitting system and aircraft - Google Patents
Aircraft transmitting system and aircraft Download PDFInfo
- Publication number
- CN116639255A CN116639255A CN202310636871.1A CN202310636871A CN116639255A CN 116639255 A CN116639255 A CN 116639255A CN 202310636871 A CN202310636871 A CN 202310636871A CN 116639255 A CN116639255 A CN 116639255A
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- aircraft
- fixed release
- fixed
- rod
- launching system
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- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000005389 magnetism Effects 0.000 description 7
- 239000003638 chemical reducing agent Substances 0.000 description 4
- WSNMPAVSZJSIMT-UHFFFAOYSA-N COc1c(C)c2COC(=O)c2c(O)c1CC(O)C1(C)CCC(=O)O1 Chemical compound COc1c(C)c2COC(=O)c2c(O)c1CC(O)C1(C)CCC(=O)O1 WSNMPAVSZJSIMT-UHFFFAOYSA-N 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention belongs to the field of auxiliary take-off equipment of aircrafts, and particularly relates to an aircraft launching system and an aircraft, wherein the aircraft launching system comprises a driving piece I and a fixed release mechanism; the output end of the driving piece I is provided with a circumferential rotation stroke or a linear movement stroke; the fixed release mechanism comprises a support, a fixed release rod and two connecting rods, wherein the support, the fixed release rod and the two connecting rods form a parallelogram mechanism, and the support and the fixed release rod are arranged opposite to each other; the fixed release rod is arranged on the fixed release rod, and the fixed release mechanism is formed by a parallelogram mechanism.
Description
Technical Field
The invention belongs to the field of auxiliary take-off equipment of aircrafts, and particularly relates to an aircraft launching system and an aircraft.
Background
The conventional take-off solution of the existing aircraft is to push the aircraft to advance by the energy of the aircraft, and the guide rail reaches the take-off speed along the runway. There are also some auxiliary take-off devices, the modes are various, but most of them need the aircraft to adapt to the complex adapting installation mechanism of the auxiliary take-off device, so that the applicability of the auxiliary take-off device is reduced, the overall design cost is improved, in addition, when the aircraft has a tail wing structure, the aircraft is easy to collide with the auxiliary take-off device, the damage of the aircraft and the auxiliary take-off device is caused, and the potential safety hazard exists.
Disclosure of Invention
The invention aims to solve the technical problem of providing an aircraft launching system capable of yielding a take-off space when an aircraft takes off and the aircraft.
The invention provides an aircraft launching system, which comprises a driving piece I and a fixed release mechanism;
the output end of the driving piece I is provided with a circumferential rotation stroke or a linear movement stroke;
the fixed release mechanism comprises a support, a fixed release rod and two connecting rods, wherein the support, the fixed release rod and the two connecting rods form a parallelogram mechanism, and the support and the fixed release rod are arranged opposite to each other;
the support is connected with the output end of the driving piece I, and the fixed release rod is provided with a fixed release structure for fixing and releasing the aircraft.
Further, the fixing and releasing mechanism also comprises a driving piece II for driving the parallelogram mechanism to deform.
Furthermore, the driving piece II is fixedly arranged on the support, the output end of the driving piece II is provided with a rotating stroke or a linear moving stroke, and the output end of the driving piece II acts on one of the connecting rods.
Still further, the fixing release mechanism further includes a locking member that maintains a state of the parallelogram mechanism.
Still further, the locking piece is including fixed electro-magnet I that sets up in the support outside and setting up the magnetism on corresponding connecting rod and inhale cooperation structure I, and electro-magnet I and magnetism inhale cooperation structure I magnetism and inhale the cooperation time, parallelogram mechanism is the rectangle state.
Furthermore, the fixed release structure is an electromagnet II arranged at two ends of the fixed release rod, and a magnetic attraction matching structure II is arranged on the aircraft corresponding to two electromagnet II parts.
Still further, the driving member i includes a rotating electric machine and a connecting arm provided on an output shaft of the rotating electric machine, and the fixing release mechanism is provided at an end of the connecting arm.
The invention also provides an aircraft suitable for the aircraft launching system, and the bottom of the aircraft is provided with a fixing structure matched with the fixing release structure.
The aircraft further includes a reset mechanism that can drive the fixed structure to retract into the interior of the fuselage of the aircraft or to retract into the interior wall of the fuselage of the aircraft.
Still further, fixed knot constructs for the arc slider, aircraft fuselage bottom is provided with the recess, and the recess bottom is provided with the through-hole that link up to fuselage inside, canceling release mechanical system is including sliding the slide bar that sets up on the through-hole and the cover is established at the slide bar and is located the reset spring of fuselage inside part, reset spring drives the slide bar towards the inside removal of fuselage, the arc slider sets up and deviates from reset spring one end at the slide bar, the arc slider with the recess adaptation.
The aircraft launching system has the beneficial effects that the fixed release mechanism formed by the parallelogram mechanism is arranged, so that the fixed release rod descends to give off a flying space when the aircraft takes off, the aircraft is prevented from colliding with the fixed release mechanism during taking off, and the use safety of the launching system is improved.
Specifically, when the driving piece I moves linearly, the speed of the driving piece I suddenly stops when the output end of the driving piece I reaches the limit position, at the moment, the parallelogram mechanism can deform through inertia, namely, the fixed release rod descends through inertia after the driving piece I is in place, so that the descending timeliness of the fixed release rod can be ensured without being provided with independent driving equipment, and when the driving piece I moves circularly, the fixed release mechanism releases the aircraft when the output end of the driving piece I reaches the set rotating speed, and then the driving piece I rapidly decelerates, at the moment, the parallelogram mechanism can also deform through inertia, namely, the fixed release rod descends through inertia after the driving piece I is in place, and the descending timeliness of the fixed release rod can be ensured without being provided with independent driving equipment.
The invention has simple and reliable integral structure, and can realize that the small aircraft can obtain the initial speed required by flying without consuming the energy of the small aircraft; for the self-unpowered aircraft, the aircraft has no engine, so that devices such as engine ignition and the like and matched facilities such as a power supply are not needed, the self-quality of the aircraft can be greatly reduced, and the flying speed of the aircraft can be provided by a transmitting system; for powered aircraft, this approach also provides the aircraft with an initial speed that is required to meet the flight stability, reducing the weight of the aircraft itself while still meeting the required speed index requirements. Therefore, the invention can also reduce the self-quality and the structural complexity of the aircraft, so that the aircraft can fly at a larger speed and a longer distance.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic structural view of the fixing and releasing mechanism in the present invention;
FIG. 3 is a schematic view of the present invention illustrating the aircraft in a pre-takeoff preparation state;
FIG. 4 is a schematic view of the state of the aircraft during take-off in the present invention;
FIG. 5 is a schematic view of the present invention after the aircraft has been launched;
FIG. 6 is a front view of an aircraft of the present invention;
FIG. 7 is a front cross-sectional view of an aircraft of the present invention;
FIG. 8 is a schematic view of the pre-takeoff preparation state at A in FIG. 7;
fig. 9 is a schematic view of the post-takeoff condition at a in fig. 7.
In the figures, 1-drive I; 11-a rotating electrical machine; 12-connecting arms; 13-a speed reducer; 14-balancing mechanism; 2-a fixed release mechanism; 21-a support; 22-a fixed release lever; 221-a limit groove; 23-connecting rods; 24-driving part II; 25-locking member; 26-an electromagnet II; 3-a controller; 4-an aircraft; 41-arc-shaped sliding blocks; 42-grooves; 43-through holes; 44-a sliding rod; 441-spring retainer plate; 45-a return spring; 5-a photoelectric switch transmitting end; and 6-a photoelectric switch receiving end.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; the device can be mechanically connected, electrically connected, physically connected or wirelessly connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical solutions of the embodiments of the present invention may be combined with each other, but it is necessary to be based on the fact that those skilled in the art can implement the technical solutions, and when the technical solutions are contradictory or cannot be implemented, the combination of the technical solutions should be considered as not existing, and not falling within the scope of protection claimed by the present invention.
As shown in fig. 1-9, the present invention provides an aircraft launching system, comprising a driving member i 1 and a fixed release mechanism 2, wherein the fixed release mechanism 2 is used for fixing an aircraft 4 and releasing the aircraft 4 to fly after the aircraft 4 reaches a set speed, and the driving member i 1 is used for providing an initial speed for the aircraft 4 fixed on the fixed release mechanism 2;
the output end of the driving piece I1 has a circumferential rotation stroke or a linear movement stroke, namely the driving piece I1 can be rotated circumferentially, such as a motor, so that the aircraft 4 takes off after being accelerated in a circumferential rotation manner, or can be moved linearly, such as an electric cylinder, an air cylinder or a hydraulic cylinder, so that the aircraft 4 takes off after being accelerated in a linear manner;
the fixed release mechanism 2 comprises a support 21, a fixed release rod 22 and two connecting rods 23, wherein the support 21, the fixed release rod 22 and the two connecting rods 23 form a parallelogram mechanism, and the support 21 and the fixed release rod 22 are arranged opposite to each other;
the support 21 is connected to the output end of the drive element i 1, and the fastening and release lever 22 is provided with a fastening and release structure for fastening and releasing the aircraft 4.
The invention can realize that the fixed release lever 22 descends to leave the flying space when the aircraft 4 takes off by arranging the fixed release mechanism 2 formed by the parallelogram mechanism, prevent the aircraft 4 from colliding with the fixed release mechanism 2 when taking off, and improve the use safety of the launching system.
Specifically, when the driving member i 1 moves linearly, the speed will suddenly stop when the output end of the driving member i 1 reaches the limit position, and at this time, the parallelogram mechanism can make the fixed release lever 22 descend by inertia after being in place, so as to ensure the descending timeliness of the fixed release lever 22 without being equipped with a separate driving device, and when the driving member i 1 moves circularly, the fixed release mechanism 2 releases the aircraft 4 when the output end of the driving member i 1 reaches the set rotation speed, and then the driving member i 1 rapidly decelerates, and at this time, the parallelogram mechanism can also make the fixed release lever 22 descend by inertia after being in place, so as to ensure the descending timeliness of the fixed release lever 22 without being equipped with a separate driving device.
The invention has simple and reliable integral structure, can realize that the small-sized aircraft 4 can obtain the initial speed required by the flight without consuming the energy of the aircraft, and is usually about 30m/s; for the self-unpowered aircraft 4, the aircraft 4 does not have an engine, so that devices such as an engine ignition device and matched facilities such as a power supply are not needed, the self-quality of the aircraft 4 can be greatly reduced, and the flying speed of the aircraft can be provided by a transmitting system; for powered aircraft 4, this also provides aircraft 4 with an initial speed that is required for stable flight, reducing the weight of aircraft 4 itself while still meeting the required speed index requirements. Therefore, the invention can also reduce the self mass and the structural complexity of the aircraft 4, so that the aircraft can fly at a larger speed and a longer distance.
In the above embodiment, the position of the parallelogram mechanism downstream of the movement direction of the driving piece i 1 may be provided with a limit structure which makes the parallelogram mechanism maintain a rectangular state when the driving piece i 1 accelerates, and when the electromagnet i is provided, the electromagnet i may be used as a limit structure. And in the case of a deceleration, the parallelogram is deformed only upstream of the direction of movement of the drive element i 1, so that it is ensured that the release lever 22 in the release mechanism 2 drops when the aircraft 4 is disengaged from the release mechanism 2.
In one embodiment, the fixed release mechanism 2 further includes a driving member ii 24 for driving the deformation of the parallelogram mechanism, in this embodiment, the deformation of the parallelogram mechanism is actively controlled by the driving member ii 24, so that the lowering operation of the fixed release lever 22 can be started before the aircraft 4 is separated from the fixed release mechanism 2, so that the aircraft 4 is separated from and lowered simultaneously with the fixed release lever 22, the possibility of collision with the fixed release mechanism 2 during the take-off of the aircraft 4 is further reduced, and meanwhile, the higher initial speed of the aircraft 4 can be provided, and the possibility of touch caused by the excessive high initial speed and the excessive low lowering speed of the fixed release lever 22 of the aircraft 4 during the passive lowering of the parallelogram mechanism is avoided.
In one embodiment, the driving element ii 24 is fixedly disposed on the support 21, the output end of the driving element ii 24 has a rotational travel or a linear travel, the output end of the driving element ii 24 acts on one of the connecting rods 23, the driving element ii 24 may be a linear travel or a rotary driving element, in a preferred embodiment, the driving element ii 24 employs a micro switch, and a rotary driving piece of the micro switch is attached to the connecting rod 23, so as to drive the connecting rod 23 to rotate.
In one embodiment, the fixed release mechanism 2 further comprises a locking member 25 for maintaining the state of the parallelogram mechanism, which can maintain the parallelogram mechanism in a constant state during acceleration of the driving member i 1, thereby improving the stability of the aircraft 4 during acceleration.
In one embodiment, the locking member 25 includes an electromagnet i fixedly disposed on the outer side of the support 21 and a magnetic attraction matching structure i disposed on the corresponding connecting rod 23, where the electromagnet i and the magnetic attraction matching structure i are in a rectangular state when in magnetic attraction matching, the magnetic attraction matching structure i may be a metal block fixedly disposed on the connecting rod 23, and the magnetic attraction matching structure i may be the connecting rod 23 itself when the connecting rod 23 itself is made of a metal material, and the locking member is fixed and released by using the electromagnet, which is simple and reliable in structure, and convenient and fast to control.
Wherein, fixed release structure can be buckle, clamping jaw etc. can be initiative or the structure of passive fixed and release aircraft 4, in one of them preferred embodiment, fixed release structure is the electro-magnet II 26 that sets up in fixed release pole 22 both ends, it is provided with magnetism to inhale cooperation structure II to correspond two electro-magnet II 26 parts on the aircraft 4, at this moment, just set up two metal pieces on the aircraft 4 and just can accomplish the quick reliable fixed and release with fixed release structure, reduce the suitability improvement of aircraft 4, when the aircraft 4 fuselage adopts the metal material to make, the aircraft 4 fuselage then can regard as magnetism to inhale cooperation structure II to use, need not to be equipped with in addition fixed knot structure, further reduces the suitability improvement of aircraft 4, simultaneously, the use of electro-magnet is reliable and stable, control convenient and fast.
In one embodiment, the driving element i 1 includes a rotating motor 11 and a connecting arm 12 disposed on an output shaft of the rotating motor 11, the fixed release mechanism 2 is disposed at an end of the connecting arm 12, in this embodiment, the driving element i 1 adopts the rotating motor 11, and relative to a linear driving manner, adopts a circumferential rotation driving manner, so that a higher speed can be provided under the condition of the same structural size, and further, a higher initial speed is provided for the aircraft 4, in a specific embodiment, the driving element i 1 further includes a speed reducer 13 disposed between the rotating motor 11 and the connecting arm 12, and a balancing mechanism 14 disposed corresponding to the connecting arm 12 is disposed at an output end of the speed reducer 13, so as to ensure stability during integral rotation.
The invention also provides an aircraft, wherein the bottom of the aircraft 4 is provided with a fixing structure matched with the fixing release structure, so that the use of the launching system is adapted.
In one embodiment, the aircraft 4 further comprises a reset mechanism, the reset mechanism can drive the fixed structure to retract into the aircraft 4 or retract into the aircraft 4, the reset mechanism is arranged to retract the fixed structure after the fixed release structure is released, so that the aerodynamic appearance of the aircraft 4 is ensured, in the embodiment, the fixed structure protrudes out of the aircraft 4 when in use, so that the aircraft 4 is at a certain height from the fixed release rod 22, other structures on the aircraft 4 can be prevented from contacting the fixed release rod 22, the stability in fixation can be improved, and the influence of the fixed structure protruding out of the aircraft 4 on the aircraft body can be avoided by arranging the reset mechanism.
In one embodiment, the fixed structure is an arc-shaped sliding block 41, a groove 42 is formed in the bottom of the aircraft 4 fuselage, a through hole 43 penetrating through the fuselage is formed in the bottom of the groove 42, the reset mechanism comprises a sliding rod 44 arranged on the through hole 43 in a sliding mode and a reset spring 45 sleeved on the inner portion of the fuselage, the end portion of the sliding rod 44 located inside the fuselage is further provided with a spring fixing plate 441, one end of the reset spring 45 is abutted to the spring fixing plate 441, the other end of the reset spring is abutted to the inner wall of the fuselage, the reset spring 45 drives the sliding rod 44 to move towards the fuselage, the arc-shaped sliding block 41 is arranged at one end of the sliding rod 44, deviating from the reset spring 45, and the arc-shaped sliding block 41 is matched with the groove 42.
In addition, the two ends of the fixed release lever 22 may be further provided with a limiting groove 221 adapted to the arc slide 41, an opening is provided at an upstream portion of the limiting groove 221 in the moving direction of the driving member i 1, after the electromagnet ii 26 is powered off, the arc slide 41 can move forward, in this embodiment, the electromagnet ii 26 is disposed at the bottom of the limiting groove 221, so when the arc slide 41 is adsorbed on the electromagnet ii 26, the arc slide 41 protrudes out of the body and is inserted into the limiting groove 221, at this time, when the aircraft 4 moves at a high speed, the main fixing force is borne by the abutting side of the arc slide 41 and the limiting groove 221, without bearing by the adsorption force of the electromagnet ii 26 alone, and in addition, after the electromagnet ii 26 is powered off, the arc slide 41 can move forward directly through the opening, and is separated from the fixed release lever 22.
In one embodiment, the invention further comprises a controller 3 and a photoelectric switch, wherein the photoelectric switch transmitting end 5 is arranged on the speed reducer 13, the photoelectric switch receiving end 6 is arranged on the connecting arm 12, and the photoelectric switch, the driving piece II 24, the electromagnet I and the electromagnet II 26 are electrically connected with the controller 3.
The electromagnet disclosed by the invention is preferably a power-off type electromagnet, namely the electromagnet keeps holding the suction force continuously in a non-energized state, and loses the magnetic force when energized, so that the suction force can be held for a long time conveniently, and the electric energy consumed by control is reduced.
The specific working flow of the invention is as follows:
in the preparation process before the take-off of the aircraft 4, when the arc-shaped sliding block 41 on the aircraft 4 is attached to the electromagnet II 26, the electromagnet II 26 is in a power-off state and keeps magnetic attraction force continuously, the electromagnet II 26 firmly adsorbs the arc-shaped sliding block 41 to finish the fixation of the aircraft 4, meanwhile, the electromagnet I is in the power-off state and keeps magnetic attraction force continuously, and the magnetic attraction matching structure I on the connecting rod 23 firmly adsorbs to ensure a rectangular state of the parallelogram mechanism;
in the take-off process of the aircraft 4, the controller 3 controls the rotating motor 11 to rotate, the rotating motor 11 drives the connecting arm 12 to rotate, then the fixed release mechanism 2 and the aircraft 4 are driven to rotate circumferentially, after the rotating motor 11 reaches a set rotating speed, the connecting arm 12 and the aircraft 4 reach a set speed, at the moment, in the next rotating period, when the photoelectric switch receiving end 6 receives a signal of the photoelectric switch transmitting end 5, the controller 3 controls the electromagnet I to be electrified, the electromagnet I loses magnetism, meanwhile, the driving piece II 24 is controlled to work, in the process that the driving piece II 24 drives the fixed release rod 22 to descend, the controller 3 controls the electromagnet II 26 to be electrified, the electromagnet II 26 loses magnetism, the fixed release mechanism 2 and the aircraft 4 are released to be fixed, and the aircraft 4 finishes take-off at the set speed.
What is not described in detail in this specification is prior art known to those skilled in the art.
Claims (10)
1. An aircraft launching system, characterized by comprising a driving element I (1) and a fixed release mechanism (2);
the output end of the driving piece I (1) is provided with a circumferential rotation stroke or a linear movement stroke;
the fixed release mechanism (2) comprises a support (21), a fixed release rod (22) and two connecting rods (23), wherein the support (21), the fixed release rod (22) and the two connecting rods (23) form a parallelogram mechanism, and the support (21) and the fixed release rod (22) are arranged oppositely;
the support (21) is connected with the output end of the driving piece I (1), and the fixed release rod (22) is provided with a fixed release structure for fixing and releasing the aircraft (4).
2. The aircraft launching system according to claim 1, characterized in that the stationary release mechanism (2) further comprises a drive element ii (24) for driving the deformation of the parallelogram mechanism.
3. An aircraft launching system according to claim 2, characterized in that the drive element ii (24) is fixedly arranged on the support (21), the output end of the drive element ii (24) having a rotational or linear movement stroke, the output end of the drive element ii (24) acting on one of the connecting rods (23).
4. The aircraft launching system according to claim 1, characterized in that the stationary release mechanism (2) further comprises a lock (25) which maintains the state of the parallelogram mechanism.
5. The aircraft launching system according to claim 4, characterized in that the locking element (25) comprises an electromagnet i fixedly arranged outside the support (21) and a magnetic attraction fitting structure i arranged on the corresponding connecting rod (23), the parallelogram mechanism being in a rectangular state when the electromagnet i and the magnetic attraction fitting structure i are magnetically attracted.
6. The aircraft launching system according to claim 1, characterized in that the fixed release structure is an electromagnet ii (26) arranged at two ends of the fixed release lever (22), and the aircraft (4) is provided with a magnetic attraction matching structure ii corresponding to two electromagnets ii (26).
7. An aircraft launching system according to any of claims 1-6, characterized in that the drive member i (1) comprises a rotating electric machine (11) and a connecting arm (12) arranged on the output shaft of the rotating electric machine (11), the stationary release mechanism (2) being arranged at the end of the connecting arm (12).
8. An aircraft adapted for use in an aircraft launching system according to any of claims 1-7, characterized in that the aircraft (4) is provided at the bottom with a fastening structure cooperating with a fastening release structure.
9. The aircraft of claim 8, further comprising a reset mechanism that drives the fixed structure to retract into the interior of the fuselage of the aircraft (4) or into the interior wall of the fuselage of the aircraft (4).
10. The aircraft according to claim 9, wherein the fixed structure is an arc-shaped sliding block (41), a groove (42) is formed in the bottom of the aircraft (4) body, a through hole (43) penetrating into the interior of the aircraft body is formed in the bottom of the groove (42), the reset mechanism comprises a sliding rod (44) arranged on the through hole (43) in a sliding mode and a reset spring (45) sleeved on the sliding rod (44) and located in the interior of the aircraft body, the reset spring (45) drives the sliding rod (44) to move towards the interior of the aircraft body, the arc-shaped sliding block (41) is arranged at one end, deviating from the reset spring (45), of the sliding rod (44), and the arc-shaped sliding block (41) is matched with the groove (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310636871.1A CN116639255A (en) | 2023-05-31 | 2023-05-31 | Aircraft transmitting system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310636871.1A CN116639255A (en) | 2023-05-31 | 2023-05-31 | Aircraft transmitting system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116639255A true CN116639255A (en) | 2023-08-25 |
Family
ID=87639592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310636871.1A Pending CN116639255A (en) | 2023-05-31 | 2023-05-31 | Aircraft transmitting system and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116639255A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117429651A (en) * | 2023-11-17 | 2024-01-23 | 广州天海翔航空科技有限公司 | Unmanned aerial vehicle catapulting device suitable for marine environment |
-
2023
- 2023-05-31 CN CN202310636871.1A patent/CN116639255A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117429651A (en) * | 2023-11-17 | 2024-01-23 | 广州天海翔航空科技有限公司 | Unmanned aerial vehicle catapulting device suitable for marine environment |
| CN117429651B (en) * | 2023-11-17 | 2024-03-19 | 广州天海翔航空科技有限公司 | Unmanned aerial vehicle catapulting device suitable for marine environment |
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