Aircraft pod structure and aircraft

Abstract

This utility model provides an aircraft parachute cabin structure and an aircraft, belonging to the technical field of flight equipment. It includes a cabin body, a locking assembly, and a canopy. The canopy is disposed on the cabin body, and the locking assembly includes at least two locking units. The canopy is connected to the cabin body via the two locking units respectively. Because the locking assembly includes at least two locking units, and the canopy is connected to the cabin body via two locking units, this utility model increases the connection structure between the canopy and the cabin body, which helps reduce the probability of the canopy accidentally opening under vibration or impact, thereby improving the flight reliability of the aircraft.

Description

Technical Field

[0001] This utility model belongs to the field of flight equipment technology, and in particular relates to an aircraft parachute cabin structure and an aircraft. Background Technology

[0002] Aircraft such as drones are typically equipped with parachutes as an emergency protection system to protect the aircraft in the event of sudden malfunctions. The parachute is usually housed inside a canopy, which is secured to the canopy via a locking mechanism. Under normal circumstances, the canopy remains locked to prevent the parachute from accidentally falling out. In an emergency, the locking mechanism unlocks, the canopy opens, and the parachute is released. Currently, the parachute deployment mechanism uses a single-point locking system, which is susceptible to vibration or impact that could cause the canopy to open accidentally, affecting the aircraft's flight stability. Utility Model Content

[0003] In view of the shortcomings of the prior art described above, the purpose of this utility model is to provide an aircraft parachute cabin structure and an aircraft to solve the problems in the prior art where the aircraft canopy is easily subjected to vibration or impact, leading to the canopy being opened accidentally.

[0004] To achieve the above and other related objectives, this utility model provides an aircraft parachute cabin structure, including a cabin body, a locking assembly, and a canopy. The canopy is disposed on the cabin body, and the locking assembly includes at least two locking units. The canopy is connected to the cabin body through the two locking units respectively.

[0005] Optionally, the locking unit includes a bolt and a locking pin that cooperates with the bolt. The bolt has an open position and a locked position. The bolt is movable between the open position and the locked position. The open position is used to disengage the locking pin from the bolt, and the locked position is used to engage the locking pin with the bolt.

[0006] The locking assembly further includes a driving unit and a reset unit, which are respectively connected to the bolt. The driving unit is used to drive the bolt to the open position, and the reset unit is used to drive the bolt to the locked position.

[0007] Optionally, the locking assembly further includes a rocker arm, the middle of which is connected to the drive unit. The drive unit drives the end of the rocker arm to swing around the middle of the rocker arm. The two ends of the rocker arm are respectively connected to the two latches to drive the latches to swing between the open position and the locked position.

[0008] Optionally, the reset unit is a tension spring, which is connected to the end of the rocker arm.

[0009] Optionally, the locking pin is disposed on the hatch cover, and the locking tongue, the drive unit, and the reset unit are disposed on the cabin body.

[0010] Optionally, one end of the hatch is hinged to the cabin body, and the other end of the hatch is connected to the cabin body via the locking unit.

[0011] Optionally, a spring-loaded mechanism is provided between the hatches, the spring-loaded mechanism being used to spring open the hatches when the locking unit is opened.

[0012] Optionally, the spring-opening mechanism is a torsion spring hinge, and the hatch is hinged to the cabin body via the torsion spring hinge.

[0013] Optionally, both locking units unlock simultaneously.

[0014] This utility model also provides an aircraft, including the parachute cabin structure as described in any of the preceding claims, wherein a parachute is disposed within the cabin.

[0015] As described above, the aircraft parachute cabin structure and aircraft of this utility model have the following beneficial effects: Since the locking assembly includes at least two locking units, the canopy is connected to the cabin body through the two locking units respectively, which increases the connection structure between the canopy and the cabin body, which helps to reduce the probability of the canopy being accidentally opened under vibration or impact, and improves the flight reliability of the aircraft. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the parachute compartment structure in an embodiment of the present utility model;

[0017] Figure 2 This is a schematic diagram of the locking component in an embodiment of the present invention.

[0018] Explanation of reference numerals in the attached drawings: 1. Cabin 2. Locking assembly 3. Torsion spring hinge 4. Output shaft 30. Locking tongue 31. Connecting rod 32. Rocker arm 33. Tension spring 34. Fixed seat 35. Guide surface 311. Detailed Implementation

[0019] The following specific embodiments illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification.

[0020] Please see Figures 1 to 2It should be understood that the structures, proportions, sizes, etc., illustrated in the accompanying drawings are merely for illustrative purposes to aid those skilled in the art and are not intended to limit the scope of this invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effectiveness and purpose of this invention, should still fall within the scope of the disclosed technical content. Furthermore, the terms "upper," "lower," "left," "right," "middle," and "one" used in this specification are merely for clarity and not intended to limit the scope of this invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of this invention.

[0021] Please see Figure 1 and Figure 2 This embodiment provides an aircraft parachute compartment structure, including a compartment 1, a locking assembly 3, and a canopy 2, with the canopy 2 disposed on the compartment 1. The compartment 1 has an opening for placing and releasing the parachute. After the canopy 2 is disposed on the compartment 1, it covers the opening of the compartment 1 to protect the parachute inside the compartment 1 and prevent the parachute from accidentally detaching from the compartment 1.

[0022] In this embodiment, the locking assembly 3 includes at least two locking units, and the canopy 2 is connected to the cabin 1 via the two locking units respectively. Since the locking assembly 3 includes at least two locking units, and the canopy 2 is connected to the cabin 1 via the two locking units, the connection structure between the canopy 2 and the cabin 1 is increased. When one locking unit unlocks due to an accident, the canopy 2 can be connected to the cabin 1 via the other locking unit, which helps reduce the probability of the canopy 2 being accidentally opened under vibration or impact, thereby improving the flight reliability of the aircraft.

[0023] In this embodiment, the two locking units unlock synchronously, which helps to improve the smoothness of parachute release and avoid parachute release delay, so as to meet the timing requirements of parachute release.

[0024] like Figure 1 As shown, in this embodiment, one end of the canopy 2 is hinged to the cabin body 1, and the other end of the canopy 2 is connected to the cabin body 1 via a locking unit. The canopy 2 is hinged to the cabin body 1 and does not need to be completely separated from it, thus enabling the canopy 2 to be reused. The hinged structure is simple, and not all connection points between the canopy 2 and the cabin body 1 need to use locking units, which helps to simplify the parachute cabin structure and reduce product costs.

[0025] In this embodiment, a spring-loaded mechanism is provided between the hatch 2 and the hatch 2, which is used to spring open the hatch 2 when the locking unit is opened. Specifically, in this embodiment, the spring-loaded mechanism is a torsion spring hinge 4, and the hatch 2 is hinged to the cabin 1 by the torsion spring hinge 4.

[0026] In this embodiment, the torsion spring hinge 4, also known as the torsion spring hinge chain, is used to connect the rear end of the canopy 2 to the cabin body 1. Normally, when the canopy 2 is closed, the torsion spring of the hinge chain is in a pre-tensioned state, storing energy. After all locking units are unlocked, the torsion spring instantly releases energy, driving the canopy 2 to spring open at an angle of 90° or more to release the parachute. The torque of the hinge torsion spring is adjustable to adjust the opening angle of the canopy 2. The torsion spring's energy storage absorbs energy during the closing process of the canopy 2, enabling the canopy 2 to open rapidly. The hinge torsion spring structure is simple, requires no continuous power consumption, and helps simplify the parachute cabin structure and reduce product energy consumption.

[0027] like Figure 2 As shown, in this embodiment, the locking unit includes a latch 31 and a locking pin that cooperates with the latch 31. The latch 31 has an open position and a locking position. The latch 31 is movably configured in the open position and the locking position. The open position is used to disengage the locking pin from the latch 31, and the locking position is used to fasten the locking pin onto the latch 31.

[0028] The locking assembly 3 also includes a drive unit and a reset unit, which are respectively connected to the bolt 31. The drive unit is used to drive the bolt 31 to the open position, and the reset unit is used to drive the bolt 31 to the locked position.

[0029] Specifically, in this embodiment, the locking assembly 3 further includes a rocker arm 33, the middle of which is connected to the drive unit. The drive unit drives the end of the rocker arm 33 to swing around the middle of the rocker arm 33. The two ends of the rocker arm 33 are respectively connected to two locking tongues 31 to drive the locking tongues 31 to swing between the open position and the locked position.

[0030] In this embodiment, the driving unit is a servo motor, and the reset unit is a tension spring 34. The servo motor drives the rocker arm 33 to rotate, and the rotation point of the rocker arm 33 is located in the middle of the rocker arm 33. The tension spring 34 is connected to the end of the rocker arm 33. The connection point of the tension spring 34 on the rocker arm 33 is far away from the rotation point of the rocker arm 33, and there is a gap between the extension direction of the tension spring 34 and the rotation point of the rocker arm 33, so that the tension spring 34 can generate a reset torque on the rocker arm 33, which facilitates pushing the latch 31 back to the locked position after the latch 31 is unlocked.

[0031] In this embodiment, the rocker arm 33 is mounted on the output shaft 30 of the servo motor. A reduction gear set is provided between the servo motor body and the output shaft 30. The servo motor drives the output shaft 30 to rotate through the reduction gear set, which in turn drives the rocker arm 33 to rotate. The reduction gear set can increase the output torque of the servo motor, so that the rocker arm 33 can overcome the reset torque of the tension spring 34 and allow the locking tongue 31 to completely disengage from the locking position, thereby ensuring the unlocking effect of the locking tongue 31.

[0032] In this embodiment, the base of the latch 31 is rotatably connected to the cabin 1. The head of the latch 31 is opposite to the locking pin in the direction of the pin's descent. The side of the latch 31 facing the locking pin is a guide surface 311, which is an inclined surface. When the hatch 2 closes, the guide surface 311 on the head of the latch 31 contacts the locking pin. The guide surface 311 engages with the locking pin, and the locking pin pushes the latch 31 to rotate, pulling the tension spring 34 until the latch 31 leaves the locking position. After the latch 31 leaves the locking position, the locking pin continues to fall until the locking pin disengages from the guide surface 311 of the latch 31, and the latch 31 resets under the action of the tension spring 34. The head of the latch 31 is provided with a wedge-shaped opening groove, which engages with the locking pin to lock it in place, thus completing the automatic locking of the hatch 2. After the locking tongue 31 is engaged with the locking pin, the tension spring 34 can keep the locking tongue 31 in the locked position, thereby resisting the interference of vibration on the locking tongue 31 and improving the reliability of the connection between the locking tongue 31 and the locking pin.

[0033] In this embodiment, the rocker arm 33 is connected to the latch 31 via a connecting rod 32. One end of the connecting rod 32 is rotatably connected to the head of the latch 31 so that the head of the latch 31 can rotate around the rotation point at the root of the latch 31. The other end of the connecting rod 32 is connected to the end of the rocker arm 33 so that when the rocker arm 33 rotates, it pulls the connecting rod 32 through the end, thereby driving the latch 31.

[0034] Specifically, in this embodiment, the locking pin is disposed on the hatch cover 2, and the locking tongue 31, the drive unit, and the reset unit are disposed on the hatch body 1. The locking pin has a relatively simple structure, and its placement on the hatch cover 2 facilitates the reduction of the overall weight of the hatch cover 2 and the ejection of the hatch cover 2.

[0035] In this embodiment, two locking pins are independently set at the front end of the hatch cover and are symmetrical about the center line of the hatch cover 2. The rudder synchronously controls the two locking tongues 31 to reciprocate between the open position and the locked position.

[0036] This embodiment also provides an aircraft, including the parachute compartment structure described above, with a parachute installed inside the compartment 1. In this embodiment, the parachute compartment cover is detachably connected to the aircraft fuselage, facilitating the replacement or maintenance of the parachute compartment structure.

[0037] In this embodiment, the cabin 1 is provided with a mounting hole for installing the locking tongue 31. The locking tongue 31 can rotate within the mounting hole. When the canopy 2 is locked, the canopy 2 is pressed down, and the locking pin of the canopy 2 slides down along the inclined surface of the upper part of the locking tongue 31, that is, the guide surface 311. When the locking pin slides to the opening slot of the locking tongue 31, the tension spring 34 drives the rocker arm 33 to rotate around the axis of the servo output shaft 30. The rotation of the rocker arm 33 drives the two connecting rods 32 to move outward to both sides of the aircraft fuselage, thereby locking the locking tongue 31 and completing the automatic locking. The servo is connected to the controller signal. When the servo receives the parachute opening signal, it rotates counterclockwise. The rotation of the rocker arm 33 drives the two connecting rods 32 to move inward to the side of the aircraft fuselage, thereby causing the corresponding locking tongue 31 to leave the locking pin of the canopy 2. The locking pin of the canopy 2 is unlocked. The canopy 2 springs open around the axis of the torsion spring hinge under the action of the torsion spring hinge. The guide parachute unfolds under the action of the airflow, bringing out the main parachute pack, and the UAV completes the parachute landing.

[0038] In summary, the aircraft parachute cabin structure and aircraft of this embodiment, since the locking assembly 3 includes at least two locking units, and the canopy 2 is connected to the cabin body 1 through the two locking units respectively, increases the connection structure between the canopy 2 and the cabin body 1, which helps to reduce the probability of the canopy 2 being accidentally opened under vibration or impact, and improves the flight reliability of the aircraft.

[0039] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A parachute compartment structure for an aircraft, characterized in that: It includes a cabin, a locking assembly, and a hatch. The hatch is disposed on the cabin, and the locking assembly includes at least two locking units. The hatch is connected to the cabin through the two locking units respectively.

2. The aircraft parachute compartment structure according to claim 1, characterized in that: The locking unit includes a bolt and a locking pin that cooperates with the bolt. The bolt has an open position and a locked position. The bolt is movable between the open position and the locked position. The open position is used to disengage the locking pin from the bolt, and the locked position is used to fasten the locking pin to the bolt. The locking assembly further includes a driving unit and a reset unit, which are respectively connected to the bolt. The driving unit is used to drive the bolt to the open position, and the reset unit is used to drive the bolt to the locked position.

3. The aircraft parachute compartment structure according to claim 2, characterized in that: The locking assembly also includes a rocker arm, the middle of which is connected to the drive unit. The drive unit drives the end of the rocker arm to swing around the middle of the rocker arm. The two ends of the rocker arm are respectively connected to the two latches to drive the latches to swing between the open position and the locked position.

4. The aircraft parachute compartment structure according to claim 3, characterized in that: The reset unit is a tension spring, which is connected to the end of the rocker arm.

5. The aircraft parachute compartment structure according to claim 2, characterized in that: The locking pin is disposed on the hatch cover, and the locking tongue, the driving unit and the reset unit are disposed on the hatch body.

6. The aircraft parachute compartment structure according to claim 1, characterized in that: One end of the hatch is hinged to the cabin body, and the other end of the hatch is connected to the cabin body via the locking unit.

7. The aircraft parachute compartment structure according to claim 6, characterized in that: A spring-loaded mechanism is provided between the hatches, and the spring-loaded mechanism is used to spring open the hatches when the locking unit is opened.

8. The aircraft parachute compartment structure according to claim 7, characterized in that: The spring-loaded mechanism is a torsion spring hinge, and the hatch is hinged to the cabin body via the torsion spring hinge.

9. The aircraft parachute compartment structure according to any one of claims 1 to 8, characterized in that: The two locking units unlock synchronously.

10. An aircraft, characterized in that: The parachute cabin structure includes any one of claims 1 to 9, wherein a parachute is disposed within the cabin.

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