CN115743557A

CN115743557A - Scaling verification machine umbrella cabin flicking mechanism

Info

Publication number: CN115743557A
Application number: CN202211621074.8A
Authority: CN
Inventors: 李毅波; 黄维宁; 徐亮; 杨永文; 孙之骏; 时雪梅
Original assignee: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co ltd
Current assignee: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co ltd
Priority date: 2022-12-16
Filing date: 2022-12-16
Publication date: 2023-03-07

Abstract

A shrinkage ratio verification machine umbrella cabin ejection mechanism belongs to the field of airplane design. Comprises an unlocking mechanism, a limiting mechanism and an ejecting mechanism. The unlocking mechanism comprises a steering engine and a steel wire rope; the steering engine is controlled by signals of the flight control system, and the steering engine arm is twisted after the signals are received to drive the steel wire rope to pull the pull rod of the limiting mechanism to move transversely, so that the unlocking function of the limiting mechanism is realized. The steel wire rope is connected with the steering engine arm and the pull rod of the limiting mechanism and used for transmitting the pulling force of the steering engine on the pull rod. The pop-up support in the pop-up mechanism is used for supporting the force transmission of the whole stay bar and the first spring. The top end of the first spring is limited through a nut arranged at the top end of the stay bar. The compressed first spring can generate a springing force so as to jack up the hatch cover at the top of the stay bar.

Description

Scaling verification machine umbrella cabin flicking mechanism

Technical Field

The invention belongs to the field of airplane design, and particularly relates to a shrinkratio verification machine umbrella cabin ejection mechanism.

Background

At present, the aircraft cannot give consideration to two modes of flight control opening and manual opening. In the process of air flight of the aircraft, if an accident occurs and normal landing cannot be realized, the emergency parachute needs to be opened, and the safety of the whole aircraft is ensured in a parachute landing mode.

The invention relates to a mechanism which can control a rudder machine to move through a flight control system to open an emergency parachute cabin of an aircraft in an air emergency state. The invention relates to an automatic flicking emergency parachute cabin cover flicking mechanism, which is characterized in that a flight control system is utilized to control a steering engine to flick a limiting mechanism of a parachute cabin cover, the parachute cabin cover bounces under the action of a spring support, under the influence of airflow, the cabin cover is separated from a machine body and a guide umbrella is pulled out, then the guide umbrella can be pulled out of a main parachute, and finally the emergency parachute landing of a model is realized.

Disclosure of Invention

The invention aims to design a set of parachute bay ejection mechanism, which can realize aerial parachute opening in an emergency state, and can meet the requirement of manual parachute opening in a ground debugging stage, thereby facilitating ground maintenance work.

An umbrella cabin ejection mechanism of a scaling verification machine comprises an unlocking mechanism, a limiting mechanism and an ejection mechanism.

The unlocking mechanism comprises a steering engine 11 and a steel wire rope 12; the steering engine 11 is controlled by signals of a flight control system, and the rudder horn is twisted after receiving the signals to drive the steel wire rope 12 to pull the pull rod 32 of the limiting mechanism to move transversely, so that the unlocking function of the limiting mechanism is realized. The steel wire rope 12 is connected with the rudder arm and the pull rod 32 of the limiting mechanism and used for transmitting the pulling force of the rudder 11 to 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 lug 35; the limiting base 31 is fixedly connected with the structural wall plate to play a role of limiting bearing, and lugs matched with the cabin cover lugs 35 and the pull rod 32 are arranged on the limiting base 31; one end of the pull rod 32 can be inserted into lug holes of the hatch cover lug 35 and the limiting base 31 and used for limiting insertion of the hatch cover lug 35, the other end of the pull rod is connected with the steering engine 11 through a steel wire rope 12, and a threaded hole is radially formed in the middle of the pull rod. The push rod 34 and the pull rod 32 are vertically screwed together through a threaded hole, so that the pull rod 32 is limited and can be manually opened from the adjacent cabin. The second spring 33 is threaded on the pull rod 32 and is positioned between the side edge of the limiting base 31 close to the steering engine 11 and the push rod 34, and the second spring mainly plays a role in pushing the push rod 34 and is used for self-locking of the whole limiting mechanism. The hatch cover lug 35 is fixed at the hatch cover end and can achieve the effect of limiting the whole hatch cover by being inserted into the pull rod 32.

The ejection mechanism comprises an ejection bracket 21, a first spring 23 and a support rod 22; the pop-up bracket 21 serves to support the force transmission of the entire stay 22, the first spring 23. Nuts are arranged at two ends of the support rod 22, the middle part of the support rod penetrates through the pop-up support 21, and the support rod can slide up and down in the pop-up support 21; a first spring 23 is sleeved on the stay bar 22 between the top nut and the pop-up support 21, and the top end of the first spring 23 is limited by a nut arranged at the top end of the stay bar 22. The compressed first spring 23 can generate a spring force to jack the hatch on top of the stay 22.

The invention has the beneficial effects that:

(1) The flight control system directly controls the cabin opening steering engine to unlock the cabin cover limiting mechanism, the design logic is simple and direct, and the control signal output of the system in an emergency state is facilitated;

(2) The ejection mechanism is designed to be of a spring type mechanical structure, and after the limiting mechanism is unlocked, the hatch cover can be ejected in the first time, so that the hatch cover is stable and reliable;

(3) The unlocking mode of the hatch cover limiting mechanism is designed into two modes of steering engine control unlocking and manual control unlocking, the steering engine control unlocking meets the requirement of emergency opening in flight, and the manual control unlocking meets the requirement of ground debugging and maintenance, so that the hatch cover limiting mechanism is more convenient to use.

(4) The aircraft can realize the parachute opening process through the flight control system in the flight process, and the safety of the aircraft is guaranteed.

Drawings

Fig. 1 an unlocking mechanism.

Fig. 2 a spacing mechanism.

Fig. 3 an ejection mechanism.

Fig. 4 illustrates.

Fig. 5 is a schematic view.

Fig. 6 uses a scene graph.

In the figure: 11, a steering engine; 12 steel wire ropes; 21 ejecting the bracket; 22 a brace bar; 23 a first spring; 31 limiting a base; 32 pull rods; 33 a second spring; 34 a push rod; 35 hatch tabs.

Detailed Description

The unlocking mechanism comprises a steering engine 11 and a steel wire rope 12; the steering engine 11 is controlled by signals of a flight control system, and the steering engine arm is twisted after the signals are received to drive the steel wire rope 12 to pull the pull rod 32 of the limiting mechanism to move transversely, so that the unlocking function of the limiting mechanism is realized. The steel wire rope 12 is connected with the pull rod 32 of the steering engine arm and the limiting mechanism and used for transmitting the pulling force of the steering engine 11 to the pull rod 32, the connection design of the steel wire rope 12 is adopted, the pulling force transmission of the steering engine 11 can be mainly met, meanwhile, when the limiting mechanism is manually opened, reverse force transmission cannot be generated to the steering engine 11, and the protection effect on the steering engine 11 is achieved.

The limiting mechanism comprises a limiting base 31, a pull rod 32, a second spring 33, a push rod 34 and a hatch cover lug 35; the limiting base 31 is connected with the structural wall plate and plays a role in main limiting bearing; the pull rod 32 is used for limiting and inserting the cabin cover lug 35, and the other end of the pull rod is connected with the steering engine 11 through the steel wire rope 12. The push rod 34 is screwed transversely to the pull rod 32, i.e. acts as a stop for the pull rod 32, and is also designed to be manually opened from the adjacent compartment. The second spring 33 mainly functions to push the push rod 34 for self-locking of the entire stopper mechanism. The hatch cover lug 35 is fixed at the hatch cover end and can achieve the effect of limiting the whole hatch cover by being inserted into the pull rod 32.

The ejection mechanism comprises an ejection bracket 21, a first spring 23 and a support rod 22; the ejection bracket 21 is used to support the force transmission of the entire stay 22, the first spring 23. The compressed first spring 23 may generate a spring force. The stay 23 is used to support the main structure of the hatch bouncing up, and the first spring 23 generates an upward force to jack up the hatch.

The working process is as follows: after the steering engine 11 receives a signal instruction of a flight control system, torsional motion is carried out, the pull rod 32 is driven to transversely pull the steel wire rope 12 to move towards the steering engine, the pull rod in an inserting state with the hatch cover lug 35 can lose a limiting effect on the hatch cover lug 35, the hatch cover which loses the limiting effect can be in a free moving state, meanwhile, the first spring 23 which is originally in a compression state can drive the support rod 22 to jack the hatch cover, the hatch cover and the appearance of a model can generate a large gap, the hatch cover can be blown away from the model under the action of airflow, a guide umbrella is taken out from the hatch cover, the guide umbrella can take a main parachute out of the guide umbrella, and emergency parachute landing is finally realized.

Claims

1. An umbrella cabin ejection mechanism of a scaling verification machine is characterized by comprising an unlocking mechanism, a limiting mechanism and an ejection mechanism;

the unlocking mechanism comprises a steering engine (11) and a steel wire rope (12); the steering engine (11) is controlled by signals of a flight control system, and the steering engine arm is twisted after receiving the signals to drive the steel wire rope (12) to pull a pull rod (32) of the limiting mechanism to move transversely, so that the unlocking function of the limiting mechanism is realized; the steel wire rope (12) is connected with the steering engine arm and a pull rod (32) of the limiting mechanism and used for transmitting the pulling force of the steering engine (11) to 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 lug (35); the limiting base (31) is fixedly connected with the structural wall plate to play a role of limiting bearing, and lugs matched with the hatch cover lugs (35) and the pull rod (32) are arranged on the limiting base (31); one end of the pull rod (32) can be inserted into lug holes of the hatch cover lug (35) and the limiting base (31) and used for limiting and inserting the hatch cover lug (35), the other end of the pull rod is connected with the steering engine (11) through a steel wire rope (12), and a threaded hole is radially formed in the middle of the pull rod; the push rod (34) and the pull rod (32) are vertically screwed together through the threaded hole; the second spring (33) penetrates through the pull rod (32) and is positioned between the side edge of the limiting base (31) close to the steering engine (11) and the push rod (34), so that the function of pushing the push rod (34) is achieved, and the self-locking of the whole limiting mechanism is realized; the hatch cover lug (35) is fixed at the hatch cover end and is positioned between the two lugs of the limiting base (31) when being inserted with the pull rod (32), so that the effect of limiting the whole hatch cover can be achieved;

the ejection mechanism comprises an ejection bracket (21), a first spring (23) and a support rod (22); the pop-up bracket (21) is used for supporting the force transmission of the stay bar (22) and the first spring (23); nuts are arranged at two ends of the support rod (22), the middle part of the support rod penetrates through the pop-up support (21), and the support rod can slide up and down in the pop-up support (21); a first spring (23) is sleeved on the supporting rod (22) between the top nut and the upper part of the pop-up support (21), and the top end of the first spring (23) is limited by a nut arranged at the top end of the supporting rod (22); the compressed first spring (23) can generate a springing force to jack the hatch cover on the top of the stay bar (22).