Composite brake parachute for airplane

Abstract

The invention provides a composite brake parachute for an aircraft, and belongs to the technical field of aircraft landing deceleration, the composite brake parachute specifically comprises a first parachute body, a plurality of second parachute bodies, a first connecting rope and a plurality of second connecting ropes, the first parachute body is connected with the tail of the aircraft through the first connecting rope, and the second parachute bodies are mutually connected through the second connecting ropes; the umbrella cloth of the first umbrella body is connected with the umbrella rope of the second umbrella body through a second connecting rope. According to the treatment scheme, the requirement for the structural strength of a single brake parachute material is lowered while the speed reduction effect and reliability of the brake parachute are improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft landing deceleration, and in particular to a composite deceleration parachute for aircraft. Background Art

[0002] Some aircraft will release parachutes to reduce their speed during landing. On the one hand, the use of parachutes can shorten the landing distance, and on the other hand, it can reduce the wear and tear on the aircraft's braking system and reduce logistics and maintenance costs.

[0003] In the existing technology, when an aircraft lands, it usually releases a parachute at the tail to reduce the speed of the aircraft. However, due to the limitation of the aircraft's altitude, the use of a large parachute will cause friction between the parachute and the ground, thus damaging the parachute. The use of a small parachute will reduce the deceleration effect of the parachute. At the same time, since there is only one parachute, when the parachute fails to be released, the parachute will not be able to play a deceleration role. On the other hand, due to the high speed of the aircraft during landing, the parachute is subjected to a large impact force at the moment of deployment, which puts forward higher requirements on the material strength of the parachute. Summary of the invention

[0004] In view of this, the present application provides a composite parachute for aircraft, which solves the problems in the prior art, improves the deceleration effect and reliability of the parachute, and reduces the requirements for the structural strength of the material of a single parachute.

[0005] The composite deceleration parachute for aircraft provided in this application adopts the following technical solution:

[0006] A composite deceleration parachute for an aircraft comprises a first parachute body, a plurality of second parachute bodies, a first connecting rope and a plurality of second connecting ropes, wherein the first parachute body is connected to the tail of the aircraft via the first connecting rope, the plurality of second parachute bodies are mutually connected via the second connecting rope, and the parachute cloth of the first parachute body is connected to a parachute rope of the second parachute body via the second connecting rope.

[0007] Optionally, a plurality of the second umbrella bodies are connected in sequence via a second connecting rope, and the umbrella cloth of a preceding second umbrella body is connected to the umbrella rope of a succeeding second umbrella body via the second connecting rope.

[0008] Optionally, the number of the second parachute bodies is two.

[0009] Optionally, the first umbrella body and the second umbrella body are consistent in structure and size.

[0010] Optionally, the composite deceleration parachute for aircraft further comprises a connecting rope release mechanism and a parachute release mechanism located inside the aircraft, wherein the parachute release mechanism is used to release the fixation of the first parachute and the second parachute so that the first parachute and the second parachute are opened; the connecting rope release mechanism is used to release the fixation of the first connecting rope and the second connecting rope so that the first parachute and the second parachute are released from the aircraft, and each of the first parachute and the second parachute is correspondingly provided with a parachute release mechanism.

[0011] Optionally, the connecting rope release mechanism includes a first release mechanism and multiple second release structures, the first release structure is used to release the fixation of the first connecting rope, so that the first connecting rope is straightened by the first parachute body, the second release mechanism and the second connecting rope correspond one to one, and one second release mechanism is used to release the fixation of one second connecting rope, so that the second connecting rope is straightened by the second parachute body.

[0012] In summary, this application includes the following beneficial technical effects:

[0013] The first parachute and the second parachute are opened when the aircraft lands, and the air acts on the aircraft to provide a force in the opposite direction of movement, thereby reducing the aircraft's running speed. By combining multiple parachute bodies, a single parachute body can use a smaller area, and the air force on a single parachute body when released is smaller, thereby reducing the requirements for the structural strength of the parachute body material. At the same time, because multiple parachute bodies are used, the superposition of the forces on the multiple parachute bodies will produce a larger force in the opposite direction of the aircraft's movement, which has a better deceleration effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0015] Figure 1 This is a schematic diagram of the overall structure of the composite deceleration parachute for the aircraft in this application.

[0016] Description of the accompanying drawings: 1. aircraft; 2. first connecting rope; 3. first parachute body; 4. second connecting rope; 5. second parachute body; 6. parachute rope; 7. parachute cloth. DETAILED DESCRIPTION

[0017] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0018] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0019] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0020] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show the components related to the present application rather than being drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0021] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0022] An embodiment of the present application provides a composite deceleration parachute for an aircraft.

[0023] like Figure 1 As shown, a composite deceleration parachute for an aircraft comprises a first parachute body 3, a plurality of second parachute bodies 5, a first connecting rope 2 and a plurality of second connecting ropes 4, wherein the first parachute body 3 is connected to the tail of an aircraft 1 via the first connecting rope 2, the plurality of second parachute bodies 5 are mutually connected via the second connecting rope 4, and the parachute cloth 7 of the first parachute body 3 is connected to a parachute rope 6 of the second parachute body 5 via the second connecting rope 4.

[0024] The plurality of second parachute bodies 5 are connected in sequence via the second connecting rope 4 , and the parachute cloth 7 of the preceding second parachute body 5 is connected to the parachute rope 6 of the following second parachute body 5 via the second connecting rope 4 .

[0025] The first parachute 3 and the second parachute 5 are opened when the aircraft 1 lands, and the air acts on the aircraft 1 to provide a force in the opposite direction of the movement, thereby reducing the speed of the aircraft 1. By combining multiple parachute bodies, a single parachute body can use a smaller area, and the air force on a single parachute body when released is smaller, thereby reducing the requirements for the structural strength of the parachute body material. At the same time, because multiple parachute bodies are used, the forces on the multiple parachute bodies are superimposed to generate a larger force in the opposite direction of the movement of the aircraft 1, which has a better deceleration effect.

[0026] The number of the second parachute bodies 5 is two.

[0027] The first umbrella body 3 and the second umbrella body 5 are consistent in structure and appearance.

[0028] The composite deceleration parachute for aircraft also includes a connecting rope release mechanism and a parachute release mechanism located in the aircraft 1. The parachute release mechanism is used to release the fixation of the first parachute 3 and the second parachute 5 so that the first parachute 3 and the second parachute 5 are opened; the connecting rope release mechanism is used to release the fixation of the first connecting rope and the second connecting rope 4 so that the first parachute 3 and the second parachute 5 are released from the aircraft 1. When the parachute is not released, the parachute is folded by the binding belt, and the parachute release mechanism releases the parachute by opening the binding belt. When the binding belt is a slipknot, the parachute release mechanism is a translation mechanism that pulls the end of the binding belt, and the telescopic end of the translation mechanism is connected to the end of the binding belt. The translation mechanism is a cylinder or a linear electric cylinder. When the binding belt is a dead knot, the parachute release mechanism can be a heating wire to burn the binding belt. The first parachute 3 and each second parachute 5 are each provided with a parachute release mechanism.

[0029] The connecting rope release mechanism includes a first release mechanism and multiple second release structures. The first release structure is used to release the fixation of the first connecting rope 2 so that the first connecting rope 2 is straightened by the first parachute body 3. The second release mechanism and the second connecting rope 4 correspond one to one. One second release mechanism is used to release the fixation of one second connecting rope 4 so that the second connecting rope 4 is straightened by the second parachute body 5.

[0030] In one embodiment, the first release structure and the second release structure are the same, both including an action mechanism, a clamping block and a pressure block, and the action mechanism of the first release structure drives the clamping block to clamp the end of the first connecting rope 2 close to the first parachute 3 on the pressure block without releasing the deceleration parachute, and the action mechanism of the second release mechanism drives the clamping block to clamp the end of the second connecting rope 4 close to the second parachute 5 on the pressure block, and the deceleration parachute is released, and the action mechanism drives the clamping block away from the pressure block, and the connecting rope is released. The action mechanism is a cylinder or a linear electric cylinder.

[0031] The plurality of second parachutes 5 are released in sequence from the rear to the front and then to the first parachute 3. When a parachute cannot be opened due to a malfunction of the parachute release mechanism, it does not affect the working state of other parachutes, and other drag parachutes can still work, thereby improving the reliability of the drag parachute. The front and back are understood as: the head of the aircraft 1 is the front.

[0032] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A composite parachute for an aircraft, characterized in that: The invention comprises a first parachute body (3), a plurality of second parachute bodies (5), a first connecting rope (2) and a plurality of second connecting ropes (4); the first parachute body (3) is connected to the tail of an aircraft (1) via the first connecting rope (2); the plurality of second parachute bodies (5) are connected to each other via the second connecting rope (4); and the parachute cloth (7) of the first parachute body (3) is connected to the parachute rope (6) of one of the second parachute bodies (5) via the second connecting rope (4).

2. The composite parachute for aircraft according to claim 1, characterized in that: A plurality of the second parachute bodies (5) are connected in sequence via a second connecting rope (4), and the parachute cloth (7) of a preceding second parachute body (5) is connected to the parachute rope (6) of a succeeding second parachute body (5) via the second connecting rope (4).

3. The composite parachute for aircraft according to claim 1, characterized in that: The number of the second parachute bodies (5) is two.

4. The composite parachute for aircraft according to claim 1, characterized in that: The first umbrella body (3) and the second umbrella body (5) are consistent in structure and appearance.

5. The composite parachute for aircraft according to claim 1, characterized in that: The composite deceleration parachute for an aircraft further comprises a connecting rope release mechanism and a parachute body release mechanism located in the aircraft (1), wherein the parachute body release mechanism is used to release the fixation of the first parachute body (3) and the second parachute body (5) so that the first parachute body (3) and the second parachute body (5) are opened; the connecting rope release mechanism is used to release the fixation of the first connecting rope (4) and the second connecting rope (4) so ​​that the first parachute body (3) and the second parachute body (5) are released from the aircraft (1), and each of the first parachute body (3) and each of the second parachute bodies (5) is provided with a parachute body release mechanism.

6. The composite parachute for aircraft according to claim 5, characterized in that: The connecting rope release mechanism comprises a first release mechanism and a plurality of second release structures, wherein the first release structure is used to release the fixation of the first connecting rope (2), so that the first connecting rope (2) is straightened by the first parachute body (3), and the second release mechanism corresponds to the second connecting rope (4) one by one, and one of the second release mechanisms is used to release the fixation of one of the second connecting ropes (4), so that the second connecting rope (4) is straightened by the second parachute body (5).

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