A parachute compartment ejection mechanism for a scaled-down verification aircraft

Abstract

A parachute compartment ejection mechanism for a scaled-down verification aircraft belongs to the field of aircraft design. It includes an unlocking mechanism, a limiting mechanism and an ejection mechanism. The unlocking mechanism includes a servo and a wire rope; the servo is controlled by a signal from a flight control system, and after receiving the signal, the servo arm is twisted, driving the wire rope to pull the pull rod of the limiting mechanism to move laterally, thereby realizing the unlocking function of the limiting mechanism. The wire rope connects the servo arm and the pull rod of the limiting mechanism, and is used to transmit the pulling force of the servo on the pull rod. The ejection bracket in the ejection mechanism is used to support the entire strut and the force transmission of the first spring. The top of the first spring is limited by a nut set at the top of the strut. The compressed first spring can generate a spring-up force, thereby lifting the hatch cover at the top of the strut.

Description

Technical Field

[0001] The invention belongs to the field of aircraft design, and in particular relates to a parachute compartment ejection mechanism of a scaled-down verification aircraft. Background Art

[0002] Currently, the aircraft cannot take into account both flight control opening and manual opening modes. If an accident occurs during the flight of the aircraft and it cannot land normally, it is necessary to open the emergency parachute and parachute to ensure the safety of the entire aircraft.

[0003] The design of the present invention is a mechanism that can realize the opening of the emergency parachute compartment of an aircraft in an emergency state in the air by controlling the movement of the servo through the flight control system. The present invention is designed as an automatic pop-up emergency parachute compartment cover pop-up mechanism, which uses the flight control system to control the servo to open the limit mechanism of the parachute compartment cover. The parachute compartment cover pops up under the action of the spring bracket, and under the influence of the airflow, the cover is separated from the aircraft body and the guide parachute is pulled out, and the guide parachute will then pull out the main parachute, and finally realize the emergency parachute landing of the model. Summary of the invention

[0004] The present invention aims to design a parachute cabin ejection mechanism, which can realize the parachute opening in the air under emergency conditions, and can also meet the needs of manual cabin opening in the ground debugging stage, so as to facilitate ground maintenance work.

[0005] A parachute compartment ejection mechanism for a scaled-down verification aircraft comprises an unlocking mechanism, a limiting mechanism and an ejection mechanism.

[0006] The unlocking mechanism includes a steering gear 11 and a steel wire 12; the steering gear 11 is controlled by a signal from the flight control system, and after receiving the signal, the steering gear arm is twisted, driving the steel wire 12 to pull the pull rod 32 of the limit mechanism to move laterally, thereby realizing the unlocking function of the limit mechanism. The steel wire 12 connects the steering gear arm and the pull rod 32 of the limit mechanism, and is used to transmit the pulling force of the steering gear 11 on the pull rod 32.

[0007] The limiting mechanism includes a limiting base 31, a pull rod 32, a second spring 33, a push rod 34, and a hatch cover ear piece 35; the limiting base 31 is fixedly connected to the structural wall plate and plays a role in limiting and bearing. The limiting base 31 is provided with an ear piece that matches the hatch cover ear piece 35 and the pull rod 32; one end of the pull rod 32 can be inserted into the ear piece hole of the hatch cover ear piece 35 and the limiting base 31, which is used for limiting and plugging the hatch cover ear piece 35, and the other end is connected to the steering gear 11 by a steel wire rope 12, and a threaded hole is radially opened in the middle. The push rod 34 and the pull rod 32 are vertically screwed together through the threaded hole, that is, the pull rod 32 plays a role in limiting the position, and is also designed to be manually opened from the adjacent cabin. The second spring 33 is passed through the pull rod 32, located between the side of the limiting base 31 close to the steering gear 11 and the push rod 34, and mainly plays the role of pushing the push rod 34, which is used for the self-locking of the entire limiting mechanism. The hatch cover ear piece 35 is fixed to the hatch cover end, and the plug connection with the pull rod 32 can achieve the function of limiting the entire hatch cover.

[0008] The pop-up mechanism includes a pop-up bracket 21, a first spring 23, and a support rod 22; the pop-up bracket 21 is used to support the force transmission of the entire support rod 22 and the first spring 23. Nuts are provided at both ends of the support rod 22, and the middle part passes through the pop-up bracket 21 and can slide up and down in the pop-up bracket 21; the first spring 23 is sleeved on the support rod 22 between the top nut and the pop-up bracket 21, and the top end of the first spring 23 is limited by the nut set at the top end of the support rod 22. The compressed first spring 23 can generate a spring-up force, thereby lifting the hatch cover at the top of the support rod 22.

[0009] Beneficial effects of the present invention:

[0010] (1) The flight control system directly controls the hatch opening servo to unlock the hatch cover limit mechanism. The design logic is relatively simple and direct, which is conducive to the control signal output of the system in an emergency state;

[0011] (2) The pop-up mechanism is designed as a spring-type mechanical structure. After the limit mechanism is unlocked, the hatch cover can be popped up immediately, which is stable and reliable;

[0012] (3) The hatch cover limiter mechanism is designed to be unlocked in two ways: servo control unlocking and manual unlocking. The servo control unlocking meets the need for emergency opening during flight, while the manual unlocking meets the need for ground debugging and maintenance, which is more convenient.

[0013] (4) The aircraft can open the parachute through the flight control system during flight, ensuring the safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 Unlocking mechanism.

[0015] Figure 2 Limiting mechanism.

[0016] Figure 3 Pop-up mechanism.

[0017] Figure 4 Graphic instructions.

[0018] Figure 5 Schematic diagram of the principle.

[0019] Figure 6 Use a scene graph.

[0020] In the figure: 11 steering gear; 12 steel wire rope; 21 pop-up bracket; 22 support rod; 23 first spring; 31 limit base; 32 pull rod; 33 second spring; 34 push rod; 35 hatch cover ear. DETAILED DESCRIPTION

[0021] The unlocking mechanism includes a steering gear 11 and a steel wire 12; the steering gear 11 is controlled by a signal from the flight control system, and after receiving the signal, the steering gear arm is twisted, driving the steel wire 12 to pull the pull rod 32 of the limit mechanism to move horizontally, thereby realizing the unlocking function of the limit mechanism. The steel wire 12 connects the steering gear arm and the pull rod 32 of the limit mechanism, and is used to transmit the pulling force of the steering gear 11 on the pull rod 32. The connection design of the steel wire 12 is mainly to meet the transmission of the pulling force of the steering gear 11, and at the same time, when the limit mechanism is manually opened, there will be no reverse force transmission to the steering gear 11, which has a protective effect on the steering gear 11.

[0022] The limiting mechanism includes a limiting base 31, a pull rod 32, a second spring 33, a push rod 34, and a hatch cover ear piece 35; the limiting base 31 is connected to the structural wall plate and plays the main role of limiting and bearing; the pull rod 32 is used for limiting and plugging the hatch cover ear piece 35, and the other end is connected to the steering gear 11 by a wire rope 12. The push rod 34 and the pull rod 32 are screwed together horizontally, that is, they play the role of limiting the pull rod 32, and are also designed to be manually opened from the adjacent cabin. The second spring 33 mainly plays the role of pushing the push rod 34, which is used for the self-locking of the entire limiting mechanism. The hatch cover ear piece 35 is fixed to the hatch cover end, and the plugging with the pull rod 32 can achieve the role of limiting the entire hatch cover.

[0023] The pop-up mechanism includes a pop-up bracket 21, a first spring 23, and a support rod 22; the pop-up bracket 21 is used to support the force transmission of the entire support rod 22 and the first spring 23. The compressed first spring 23 can generate a pop-up force. The support rod 23 is used to support the main structure of the hatch cover to pop up, and the first spring 23 generates an upward force to lift the hatch cover.

[0024] Working process: after receiving the signal command from the flight control system, the servo 11 performs a twisting motion, driving the wire rope 12 to pull the pull rod 32 laterally toward the servo, so that the pull rod which is in a plug-in state with the hatch cover ear 35 will lose its limiting effect on the hatch cover ear 35, and the hatch that loses the limit will be in a freely movable state. At the same time, the first spring 23 which was originally in a compressed state will drive the strut 22 to lift the hatch cover, so that a larger gap will be generated between the hatch cover and the model shape, so that under the action of the airflow, the hatch cover will be blown away from the model, thereby bringing out the guide parachute, which in turn brings out the main parachute, and finally achieves an emergency parachute landing.

Claims

1. A parachute compartment ejection mechanism for a scaled verification aircraft, characterized in that: Including unlocking mechanism, limiting mechanism and ejecting mechanism; The unlocking mechanism comprises a steering gear (11) and a steel wire rope (12); the steering gear (11) is controlled by a signal from a flight control system, and after receiving the signal, the steering gear arm is twisted, driving the steel wire rope (12) to pull the pull rod (32) of the limiting mechanism to move laterally, thereby realizing the unlocking function of the limiting mechanism; the steel wire rope (12) connects the steering gear arm and the pull rod (32) of the limiting mechanism, and is used to transmit the pulling force of the steering gear (11) on the pull rod (32); The limiting mechanism comprises a limiting base (31), a pull rod (32), a second spring (33), a push rod (34), and a hatch cover ear piece (35); the limiting base (31) is fixedly connected to the structural wall plate to play a role in limiting and bearing force, and the limiting base (31) is provided with an ear piece that is compatible with the hatch cover ear piece (35) and the pull rod (32); one end of the pull rod (32) can be inserted into the hatch cover ear piece (35) and the ear piece hole of the limiting base (31) for limiting plugging of the hatch cover ear piece (35), and the other end is connected to the steering gear (11) with a steel The wire rope (12) is connected, and a threaded hole is radially provided in the middle; the push rod (34) and the pull rod (32) are vertically screwed together through the threaded hole; the second spring (33) is passed through the pull rod (32), and is located between the side of the limit base (31) close to the steering gear (11) and the push rod (34), and plays a role in pushing the push rod (34) to achieve self-locking of the entire limit mechanism; the hatch cover ear piece (35) is fixed to the hatch cover end, and when plugged with the pull rod (32), it is located between the two ear pieces of the limit base (31), which can achieve the function of limiting the entire hatch cover; The pop-up mechanism comprises a pop-up bracket (21), a first spring (23), and a support rod (22); the pop-up bracket (21) is used to support the force transmission of the support rod (22) and the first spring (23); nuts are provided at both ends of the support rod (22), the middle part of which passes through the pop-up bracket (21) and can slide up and down in the pop-up bracket (21); the first spring (23) is sleeved on the support rod (22) between the top nut and the top of the pop-up bracket (21), and the top end of the first spring (23) is limited by the nut arranged at the top end of the support rod (22); the compressed first spring (23) can generate a spring-up force, thereby lifting the hatch cover at the top of the support rod (22).

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