CN112678207B - Reentry attitude adjusting device of small aircraft - Google Patents
Reentry attitude adjusting device of small aircraft Download PDFInfo
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- CN112678207B CN112678207B CN202110035373.2A CN202110035373A CN112678207B CN 112678207 B CN112678207 B CN 112678207B CN 202110035373 A CN202110035373 A CN 202110035373A CN 112678207 B CN112678207 B CN 112678207B
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Abstract
The invention discloses a loading attitude adjusting device of a small aircraft, which relates to the field of aircrafts and comprises an attitude adjusting umbrella, a connecting rope, an installation cabin, a breaking rope and a cutting assembly; the attitude of the aircraft is adjusted through the attitude adjusting umbrella, the connecting rope between the attitude adjusting umbrella and the cabin body is cut at regular time by combining the cutting assembly, after the aircraft is finally adjusted to a certain height, the flying speed is increased along with the increase of air density along with the reduction of the height, the dynamic pressure of the attitude adjusting umbrella is increased, when the pulling force formed by the dynamic pressure exceeds the design value of the snapping rope, the snapping rope breaks the connection between the cabin body and the attitude adjusting umbrella, the inertia of the aircraft is re-entered, the attitude adjusting control of the aircraft is completed, the device has simple structure and lower cost, and the required space volume is smaller; the device does not need additional energy requirements such as power supply and the like, can complete all time sequence actions from parachute opening, posture adjustment to separation, can effectively reduce the flight attack angle in the reentry process of the aircraft, and provides a simple, reliable and economical technical method for reentry posture adjustment of the small aircraft.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a reentry posture adjusting device of a small aircraft.
Background
Before the high-speed aircraft reenters, the flight attitude of the high-speed aircraft is generally required to be controlled, so that the aircraft reenters in a state of a small attack angle to improve the reentry speed and stability, the reentry height is generally 20-100 km, the air is thin, and the air rudder at the moment is difficult to provide effective control torque, so the attitude of the aircraft is usually adjusted by adopting a direct force control method such as a rocket engine and the like in the traditional method, but the direct force control method is complex in system implementation, high in cost and not suitable for small aircraft.
Disclosure of Invention
The invention aims to solve the problems and designs a reentry attitude adjusting device of a small aircraft.
The invention realizes the purpose through the following technical scheme:
the reentry attitude adjusting device of the small aircraft comprises an attitude adjusting umbrella, a connecting rope, an installation cabin and a cutting assembly, wherein one end of the attitude adjusting umbrella is connected with the interior of a cabin body of the installation cabin through the connecting rope, the installation cabin is fixedly installed at the tail part of the aircraft, an umbrella ejecting cylinder for ejecting a parachute is fixed on a cabin cover of the installation cabin, and the cutting assembly is used for cutting off the connecting rope; before the posture is adjusted, the segmentation component and the posture adjusting umbrella are positioned in the cabin body, when the posture is required to be adjusted, the cabin cover is separated from the cabin body, the posture adjusting umbrella is popped out and unfolded, and two ends of the connecting rope respectively have a tensile force effect with the posture adjusting umbrella and the cabin body; the posture adjusting umbrella is separated from the mounting cabin after the posture adjustment is finished.
The invention has the beneficial effects that: the attitude of the aircraft is adjusted through the attitude adjusting umbrella, the connecting rope between the attitude adjusting umbrella and the cabin body is cut at regular time by combining the cutting assembly, finally, after the attitude adjusting is finished, the aircraft enters a certain height again, the flying speed is increased along with the increase of the air density along with the reduction of the height, the dynamic pressure of the attitude adjusting umbrella is gradually increased at the moment, when the pulling force formed by the dynamic pressure exceeds the bearing design value of the snapping rope, the snapping rope breaks the connection between the cabin body and the attitude adjusting umbrella, the inertia of the aircraft enters again, the attitude adjusting control of the aircraft is finished, the device has a simple structure and lower cost, and the required space volume is smaller; the device does not need extra energy requirements such as power supply and the like, can complete all time sequence actions from parachute opening, attitude adjustment to separation, can effectively reduce the flight attack angle in the reentry process of the aircraft, and provides a simple, reliable and economic technical method for reentry attitude adjustment of the small aircraft.
Drawings
FIG. 1 is a schematic structural diagram of a reentry attitude adjusting device of a small aircraft according to the present invention;
wherein corresponding reference numerals are:
1-umbrella cover; 2-bouncing an umbrella cylinder; 3-posture adjusting umbrella; 4-breaking the rope; 5-time delay cutter; 6-connecting a rope; 7-a cabin; 8-an aircraft.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be further noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" and the like are to be broadly construed, for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The following detailed description of embodiments of the invention refers to the accompanying drawings.
As shown in fig. 1, the re-entering posture-adjusting device of the small aircraft comprises a posture-adjusting umbrella 3, a connecting rope 6, an installation cabin and a dividing component, wherein one end of the posture-adjusting umbrella 3 is connected with the interior of a cabin body 7 of the installation cabin through the connecting rope 6, the installation cabin is fixedly installed at the tail part of the aircraft 8, an umbrella ejecting cylinder 2 for ejecting the posture-adjusting umbrella 3 is fixed on a cabin cover of the installation cabin, and the dividing component is used for cutting off the connecting rope 6; before the posture is adjusted, the dividing assembly and the posture adjusting umbrella 3 are positioned in the cabin body 7, when the posture is required to be adjusted, the cabin cover is separated from the cabin body 7, the posture adjusting umbrella 3 pops out and unfolds, and two ends of the connecting rope 6 respectively have a pulling force effect with the posture adjusting umbrella 3 and the cabin body 7; the posture adjusting umbrella 3 is separated from the installation cabin after the posture adjustment is finished.
The cutting component is a time-delay cutter 5, the time-delay cutter 5 is arranged at one end of the connecting rope 6 close to the cabin body 7, and the cutting action end of the time-delay cutter 5 acts on the connecting rope 6.
The posture correcting device further comprises a breaking rope 4, two ends of the breaking rope 4 are fixedly connected with the inside of the posture correcting umbrella 3 and the cabin body 7 respectively, and the length of the breaking rope 4 is larger than that of the connecting rope 6.
The working principle of the reentry attitude adjusting device of the small aircraft is as follows:
the installation cabin is installed at the tail of an aircraft 8, before working, the parachute ejecting barrel, the posture adjusting parachute 3, the snapping rope 4, the time delay cutter 5 and the connecting rope 6 are all arranged inside a cabin body 7 of the installation cabin, and the cabin cover is closed at an outlet of the cabin body 7 towards the tail direction.
Before the aircraft 8 enters again, the parachute ejecting cylinder is triggered to act, the cabin cover is opened, the posture adjusting parachute 3 is thrown out, the posture adjusting parachute 3 is inflated to complete parachute opening, the connecting rope 6 is straightened, meanwhile, the time delay cutter 5 is triggered to start timing, at the moment, the length of the snapping rope 4 is larger than that of the connecting rope 6, the snapping rope 4 is in a loose state and cannot be impacted by dynamic load of parachute opening, after the set time delay time, the posture adjusting parachute 3 finishes parachute opening and stabilization, the time delay cutter 5 cuts off the connecting rope 6, the snapping rope 4 is straightened, the cabin body 7 and the posture adjusting parachute 3 are connected through the snapping rope 4, the aircraft 8 descends under the stabilizing effect of the posture adjusting parachute 3 to gradually reduce the flight attack angle, and then the stable posture is kept for flying to enter again.
After the aircraft 8 reenters to a certain height, the air density is increased along with the reduction of the height, the flying speed is increased, the dynamic pressure of the attitude adjusting umbrella 3 is gradually increased, when the pulling force formed by the dynamic pressure exceeds the bearing design value of the snapping rope 4, the snapping rope 4 breaks the connection between the cabin body 7 and the attitude adjusting umbrella 3, the inertia of the aircraft 8 reenters, and the attitude adjusting is completed.
The attitude of the aircraft 8 is adjusted through the attitude adjusting umbrella 3, the connecting rope 6 between the attitude adjusting umbrella 3 and the cabin body 7 is cut at regular time by combining a cutting assembly, finally, after the attitude adjusting is finished, the aircraft 8 enters a certain height again, the flying speed is increased along with the reduction of the height after the air density is increased, the dynamic pressure of the attitude adjusting umbrella 3 is gradually increased, when the pulling force formed by the dynamic pressure exceeds the design value of the load bearing of the snapping rope 4, the snapping rope 4 breaks the connection between the cabin body 7 and the attitude adjusting umbrella 3, the aircraft 8 enters again through inertia, the attitude adjusting control of the aircraft 8 is finished, the device is simple in structure, the cost is low, and the required space volume is small; and the device does not need extra energy requirements such as power supply and the like, can complete all time sequence actions from parachute opening, posture adjustment to separation, can effectively reduce the flight attack angle in the reentry process of the aircraft 8, and provides a simple, reliable and economic technical method for the reentry posture adjustment of the small aircraft 8.
The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.
Claims (2)
1. Reentry of small aircraft transfers appearance device, its characterized in that: the device comprises a posture adjusting umbrella, a connecting rope, an installation cabin and a dividing assembly, wherein one end of the posture adjusting umbrella is connected with the interior of a cabin body of the installation cabin through the connecting rope, the installation cabin is fixedly installed at the tail part of an aircraft, an umbrella ejecting cylinder for ejecting a parachute is fixedly arranged on a cabin cover of the installation cabin, and the dividing assembly is used for cutting off the connecting rope; before the posture is adjusted, the dividing assembly and the posture adjusting umbrella are positioned in the cabin body, when the posture is required to be adjusted, the cabin cover is separated from the cabin body, the posture adjusting umbrella is popped out and unfolded, and two ends of the connecting rope respectively have a tensile force effect with the posture adjusting umbrella and the cabin body; the posture adjusting umbrella is separated from the installation cabin after the posture adjustment is finished, the posture adjusting device is put in the cabin, the posture adjusting umbrella further comprises a pull-off rope, two ends of the pull-off rope are fixedly connected with the posture adjusting umbrella and the interior of the cabin respectively, and the length of the pull-off rope is larger than that of the connecting rope.
2. The reentry attitude adjusting device of a small aircraft according to claim 1, characterized in that: the cutting assembly is a time-delay cutter which is arranged at one end of the connecting rope close to the cabin body, and the cutting action end of the time-delay cutter acts on the connecting rope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110035373.2A CN112678207B (en) | 2021-01-12 | 2021-01-12 | Reentry attitude adjusting device of small aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110035373.2A CN112678207B (en) | 2021-01-12 | 2021-01-12 | Reentry attitude adjusting device of small aircraft |
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| CN112678207A CN112678207A (en) | 2021-04-20 |
| CN112678207B true CN112678207B (en) | 2022-12-13 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007182182A (en) * | 2006-01-10 | 2007-07-19 | Ihi Aerospace Co Ltd | Recovery method and recovery device for returning member returned at high speed |
| CN106446442A (en) * | 2016-10-12 | 2017-02-22 | 北京理工大学 | Parachute unfolding process stability assessment method of Mars parachute bag combination |
| CN206437224U (en) * | 2017-01-24 | 2017-08-25 | 湖北德睿四通科技有限公司 | A kind of escape chute falling unit for multi-rotor unmanned aerial vehicle |
| CN109250154A (en) * | 2018-09-07 | 2019-01-22 | 陕西中天火箭技术股份有限公司 | A kind of secondary parachute-opening safety landing system in side |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB742587A (en) * | 1952-11-10 | 1955-12-30 | Ca Nat Research Council | Parachute |
| CN2288138Y (en) * | 1996-06-14 | 1998-08-19 | 任义军 | Parachute for astronautic re-entry spacecraft |
| US8047472B1 (en) * | 2006-06-06 | 2011-11-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Ram booster |
| US8608112B1 (en) * | 2007-02-28 | 2013-12-17 | ALD Systems, Inc. | Modular programmable electronic initiation device for parachute disreefing or disconnect |
| JP5022113B2 (en) * | 2007-06-08 | 2012-09-12 | 藤倉航装株式会社 | Parachute leafing device |
| KR101579567B1 (en) * | 2010-02-11 | 2015-12-22 | 호워드 엠. 친 | Rocket launch system |
| JP6243768B2 (en) * | 2014-03-25 | 2017-12-06 | 株式会社Ｉｈｉエアロスペース | Method for opening flying object and parachute |
| CN204415737U (en) * | 2015-01-28 | 2015-06-24 | 湖南基石信息技术有限公司 | A kind of four rotor wing unmanned aerial vehicle overheads help and fall umbrella |
| CN205203355U (en) * | 2015-12-04 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Umbrella cabin is thrown and is covered structure |
| US11459113B2 (en) * | 2016-07-11 | 2022-10-04 | Kitty Hawk Corporation | Multimodal aircraft recovery system |
| US10669047B2 (en) * | 2017-05-24 | 2020-06-02 | The Boeing Company | System and method for hypersonic payload separation |
| WO2019035378A1 (en) * | 2017-08-17 | 2019-02-21 | 臼井 芳雄 | Spacecraft and debris removal system |
| US9981749B1 (en) * | 2017-10-13 | 2018-05-29 | Kitty Hawk Corporation | Parachute deployment system using decoupled tow and release lines |
| CN109850164B (en) * | 2019-03-27 | 2023-06-27 | 河南机电职业学院 | Unmanned aerial vehicle parachuting recovery device and recovery method thereof |
| CN209834020U (en) * | 2019-04-05 | 2019-12-24 | 湖南浩天翼航空技术有限公司 | Automatic umbrella device of cutting of unmanned aerial vehicle |
-
2021
- 2021-01-12 CN CN202110035373.2A patent/CN112678207B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007182182A (en) * | 2006-01-10 | 2007-07-19 | Ihi Aerospace Co Ltd | Recovery method and recovery device for returning member returned at high speed |
| CN106446442A (en) * | 2016-10-12 | 2017-02-22 | 北京理工大学 | Parachute unfolding process stability assessment method of Mars parachute bag combination |
| CN206437224U (en) * | 2017-01-24 | 2017-08-25 | 湖北德睿四通科技有限公司 | A kind of escape chute falling unit for multi-rotor unmanned aerial vehicle |
| CN109250154A (en) * | 2018-09-07 | 2019-01-22 | 陕西中天火箭技术股份有限公司 | A kind of secondary parachute-opening safety landing system in side |
Non-Patent Citations (1)
| Title |
|---|
| 射伞火箭开伞过程动力学仿真与分析;刘涛;《航天返回与遥感》;20200815;第31-37页 * |
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