CN110498064A - A kind of fairing of launch vehicle recovery scheme - Google Patents
A kind of fairing of launch vehicle recovery scheme Download PDFInfo
- Publication number
- CN110498064A CN110498064A CN201910877409.4A CN201910877409A CN110498064A CN 110498064 A CN110498064 A CN 110498064A CN 201910877409 A CN201910877409 A CN 201910877409A CN 110498064 A CN110498064 A CN 110498064A
- Authority
- CN
- China
- Prior art keywords
- radome fairing
- fairing
- lateral jet
- spout
- launch vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000011084 recovery Methods 0.000 title claims abstract description 17
- 230000000694 effects Effects 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 9
- 238000004064 recycling Methods 0.000 abstract description 9
- 230000003139 buffering effect Effects 0.000 abstract description 3
- 230000006378 damage Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007963 capsule composition Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/78—Parachutes in association with other load-retarding apparatus
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
A kind of fairing of launch vehicle recovery scheme, can be used for fairing of launch vehicle safe retrieving, and by the way of " parachuting+Lateral jet+air bag ", the program is mainly made of parachute, Lateral jet device and air bag；Parachute is mainly made of umbrella cover, hidden discount, rope；Lateral jet device mainly by closed shell, hydraulic device, hydraulic actuator, Lateral jet cluster engine at；Air bag is mainly made of closed shell, airbag body, high pressure inflator.Parachute can significantly be slowed down, and Lateral jet is used for rail control, and air bag is for recycling latter end landing and buffering.The present invention can enhance radome fairing removal process stability by the way of " parachuting+Lateral jet+air bag ", improve radome fairing drop point accuracy, promote radome fairing landing and buffering performance, have many advantages, such as high reliablity, at low cost.
Description
Technical field
The present invention relates to a kind of fairing of launch vehicle recovery schemes, are suitable for reusable carrier rocket field.
Background technique
In space launch vehicle transmitting field, there is numerous radiation patterns, wherein most noticeable is how to realize
The reuse of carrier rocket is to reduce launch cost.The related reusable research of carrier rocket has become space industry
Hot issue.Earlier US Aeronautics and Space Administration attempts to solve the problems, such as this by space shuttle, and borrow transmit cycle is short, emitting times
More features improves tranmitting frequency to reduce cost, and final because overhauling, cost is excessively high and multiple generation space flight accident and comes to an end.
Hereafter it reuses space launch vehicle field gradually to develop as the recycling of part rocket body and reuse the stage, this time
Debit's formula, which refers to, installs thrust control recovery system additional to the component part of carrier rocket, to realize recycle without damage.U.S. Space
No. nine rocket radome fairings recycling of X company falcon use parachuting provide slow down, end capture ship track it is close by the way of, and pass through
Practical application demonstrates a kind of radome fairing recovery scheme with certain feasibility.But since recyclable radome fairing does not have
Autonomous control system, therefore on the one hand, recycling capture difficulty is big, on the other hand, proposes to capture mechanism very high motor-driven, slow
Technical requirements, the success rates such as punching are lower.
Summary of the invention
Technical problem solved by the present invention is existing radome fairing removal process is overcome to fall without control, the uncontrollable skill of drop point
Art is insufficient, provides the fairing of launch vehicle recovery scheme of a kind of " parachuting+Lateral jet+air bag ".
Solution of the invention are as follows: a kind of fairing of launch vehicle recovery scheme can be used for fairing of launch vehicle and return
It receives, is mainly made of parachute, Lateral jet device and air bag, it is characterised in that: parachute includes: umbrella cover, hidden discount and rope；Side
Jet apparatus includes: Lateral jet spout, section spout, closed shell, hydraulic device and hydraulic actuator；Air bag includes: air bag
Ontology, closed shell, high pressure inflator.
The umbrella cover is installed on the inside of radome fairing, is connected to hidden discount with rope and is installed on radome fairing outer edge.In delivery fire
Arrow ascent stage is collapsed in the inside of radome fairing, and throwing radome fairing movement when carrier rocket terminates, and radome fairing decrease speed is stablized
Afterwards, umbrella cover is opened, and radome fairing speed is greatly reduced.The Lateral jet spout 1 is installed on rear side of radome fairing, passes through hydraulic device
The direction of Lateral jet spout is controlled with hydraulic actuator.When close to ground, Lateral jet spout passes through injection high pressure gas control
The posture and whereabouts track of radome fairing processed.The Lateral jet spout 2 is installed on section spout internal and Lateral jet spout 2 and section
In same plane, work, the closed shell being connected on the outside of the spout of section with radome fairing falls off nozzle, sprays Lateral jet
Mouth 2 is exposed.The section spout is located at radome fairing upper end 1/3, section and radome fairing flush with outer surface, in the effect of Lateral jet
Radome fairing can be made to be changed airbag body described in fall trajectory by the effect of thrust down to be installed on the inside of radome fairing, landed
Airbag body is extruded closed shell by high pressure inflator, while the disconnection of hidden discount rope is prevented radome fairing by preceding 10 seconds
It turns on one's side.
The principle of above scheme is: when carrier rocket emits, recyclable device is installed on 1 inner surface of radome fairing, and quality point
Cloth does not influence emission process, and after radome fairing is dished out, umbrella cover is unfolded under the action of high-speed flow, is substantially subtracted to radome fairing
Speed recycles middle section in radome fairing, and Lateral jet device controls Lateral jet spout direction, realization pair under the action of hydraulic actuator
The control of thrust direction controls posture and fall trajectory in radome fairing dropping process.Latter end is recycled in radome fairing, high pressure is filled
Device of air starting, squeezes out air bag from closed shell, and inflates to air bag rapidly, whole below radome fairing after airbag deployment
Body paves, and reduces the buffering of radome fairing landing moment.To realize the safe pinpoint landing recycling of radome fairing.
Compared with prior art, the beneficial effects of the present invention are: the present invention provides a kind of three-in-one way of recycling, with
Single parachuting recovery method is compared, and method proposed by the present invention is not in the case where influencing carrier rocket normal flight, Ke Yishi
The accurate positioning of existing radome fairing recycling, effectively avoids damage of the overload to radome fairing rocket body in radome fairing removal process, thus
Radome fairing recycling reliability is improved, reduces and reuses cost.
Detailed description of the invention
Fig. 1 is the structure chart of parachute opening state of the present invention.
Fig. 2 is the top view on the outside of radome fairing of the present invention.
Fig. 3 is the top view of Lateral jet device of the present invention.
Fig. 4 is the top view on the inside of radome fairing of the present invention.
In figure: 1- umbrella cover, 2- hidden discount, 3- rope, 4A- Lateral jet spout, 4B- Lateral jet spout, the section 5- spout, 6A-
The closed shell of closed shell, 6B-, 7- hydraulic device, 8- hydraulic actuator, 9- airbag body, 10- high pressure inflator, 11- are whole
Stream cover.
Specific embodiment
In conjunction with attached drawing of the present invention, technical solution in the embodiment of the present invention is described in detail, specific as follows:
It is mainly gentle by parachute, Lateral jet device to please refer to Fig.1 to Fig.4 the recovery system designed in the recovery scheme
Capsule composition, wherein parachute includes: umbrella cover (1), hidden discount (2), rope (3)；Lateral jet device include: Lateral jet spout (4A,
4B), section spout (5), closed shell (6A), hydraulic device (7) and hydraulic actuator (8)；Air bag includes: air bag (9), closed
Shell (6B), high pressure inflator (10)；Recycle object: radome fairing (11)；Umbrella cover (1) is located on the inside of radome fairing (11), is used in combination
Rope (3) is fixed on hidden discount (2), and hidden discount (2) is installed on radome fairing (11) outer edge, and Lateral jet spout 1 (4A) is located at rectification
It covers on rear side of (11), Lateral jet spout 2 (4B) is installed on section spout (5) inside, and Lateral jet spout 2 (4B) and section spout
(5) be in same plane, closed shell (6A) is located on the outside of section spout (5) to be connected with radome fairing (11), hydraulic device (7) with
Hydraulic actuator (8) is located at below Lateral jet spout (4A, 4B), and air bag (9) is located at radome fairing (11) inner surface and closed shell
(6B) overlapping position, high pressure inflator (10) are installed on the left side of air bag (9).
It rises on the launch vehicle the stage, umbrella cover (1) is located inside and the closed housing of radome fairing (11) with air bag (9)
The inside of body (6B), Lateral jet spout 1 (4A) are symmetrically arranged on the rear side of radome fairing (11), and Lateral jet spout 2 (4B) is installed on
The section spout (5) of front side, high pressure inflator (10) are installed on the left of closed shell (6B), and all devices are symmetrically distributed in
Radome fairing (11), does not influence carrier rocket ascent stage aerial mission.
Radome fairing (11) is dished out the stage, when radome fairing (11) speed, which reaches, stablizes maximum speed, unlocks rope automatically
(3), umbrella cover (1) is made to be detached from radome fairing (11), umbrella cover (1) is unfolded rapidly under action of high-speed airflow, and radome fairing (11) is made to fall
Speed is greatly decreased.
Radome fairing (11) recycles middle section, and the speed of radome fairing (11) is greatly reduced, hydraulic device (7) starting, and in actuation
Under cylinder (8) effect, the direction Lateral jet spout 1 (4A) is controlled, allows to move left and right, while closed housing on front side of radome fairing (11)
Body (6A) falls off, and so that Lateral jet spout 2 (4B) is carried out parallel injection inside section spout (5), passes through two Lateral jets of rear side
Lateral jet (4B) mating reaction in (4A) and front side section spout controls the posture in radome fairing (11) dropping process and whereabouts
Trajectory.
Radome fairing (11) recycles latter end, and before landing is completed 10 seconds, closed shell (6B) falls off, in high pressure inflator (10)
Under effect, airbag body (9) passes through closed body clearance along radome fairing (11) outwardly deploying, and rapidly to airbag body (9)
Inflation, whole below radome fairing (11) after airbag body (9) expansion to pave, when that will land 1-2 seconds, hidden discount (2) will restrict
Rope (3) disconnects, and radome fairing (11) is avoided after landing thus may be used because secondary injury occurs ground is by airflow influence for umbrella cover (1)
Realize the safe pinpoint landing recycling of radome fairing (11).
Claims (6)
1. a kind of fairing of launch vehicle recovery scheme is mainly made of parachute, Lateral jet device and air bag, feature exists
In: parachute includes: umbrella cover (1), hidden discount (2) and rope (3)；Lateral jet device includes: Lateral jet spout (4A, 4B), section
Spout (5), closed shell (6A), hydraulic device (7) and hydraulic actuator (8)；Air bag includes: airbag body (9), closed shell
(6B), high pressure inflator (10).
2. a kind of fairing of launch vehicle recovery scheme according to claim 1, it is characterised in that: umbrella cover (1) peace
Loaded on the inside of radome fairing (11), hidden discount (2) is connected to rope (3) and is installed on radome fairing (11) outer edge.On the launch vehicle
The stage of liter collapses in the inside of radome fairing (11), and throwing radome fairing movement when carrier rocket terminates, and radome fairing decrease speed is stablized
Afterwards, umbrella cover (1) is opened, and radome fairing speed is greatly reduced.
3. a kind of fairing of launch vehicle recovery scheme according to claim 1, it is characterised in that: the Lateral jet spout
1 (4A) is installed on rear side of radome fairing (11), controlled by hydraulic device (7) and hydraulic actuator (8) Lateral jet spout (4A,
Direction 4B).When close to ground, Lateral jet spout (4A, 4B) controls the posture of radome fairing (11) by injection high pressure gas
With whereabouts track.
4. a kind of fairing of launch vehicle recovery scheme according to claim 1, it is characterised in that: the Lateral jet spout
2 (4B) are installed on section spout (5) internal and Lateral jet spout 2 (4B) and section spout (5) are in same plane, when work,
The closed shell (6A) being connected on the outside of section spout (5) with radome fairing (11) falls off, and keeps Lateral jet spout 2 (4B) exposed.
5. a kind of fairing of launch vehicle recovery scheme according to claim 1, it is characterised in that: the section spout
(5) it is located at radome fairing (11) upper end 1/3, section and radome fairing flush with outer surface can make whole under the action of Lateral jet
Stream cover (11) is changed fall trajectory by the effect of thrust.
6. a kind of fairing of launch vehicle recovery scheme according to claim 1, it is characterised in that: the airbag body
(9) it is installed on the inside of radome fairing (11), 10 seconds before landing, extrudes airbag body (9) by high pressure inflator (10)
Closed shell (10), and inflation is in the side of radome fairing (11) towards ground within 0.1 second time, to protect radome fairing
Safe landing.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910865184 | 2019-09-12 | ||
| CN2019108651840 | 2019-09-12 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110498064A true CN110498064A (en) | 2019-11-26 |
Family
ID=68592056
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910877409.4A Pending CN110498064A (en) | 2019-09-12 | 2019-09-17 | A kind of fairing of launch vehicle recovery scheme |
Country Status (1)
| Country | Link |
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| CN (1) | CN110498064A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846246A (en) * | 2020-07-08 | 2020-10-30 | 中北大学 | Portable single reverse-spraying soft landing safety protection device and using method thereof |
| CN112429278A (en) * | 2020-11-11 | 2021-03-02 | 陕西中天火箭技术股份有限公司 | Firer ejection recovery mechanism |
| CN112556515A (en) * | 2021-02-19 | 2021-03-26 | 北京星际荣耀空间科技股份有限公司 | Recovery system and method for rocket fairing |
| CN113022840A (en) * | 2021-04-13 | 2021-06-25 | 中国人民解放军战略支援部队航天工程大学 | Flexible variant airship for recycling fairing of carrier rocket and recycling method |
| RU2792472C1 (en) * | 2022-12-05 | 2023-03-22 | Федеральное государственное автономное образовательное учреждение высшего образования "Омский государственный технический университет" | Method for saving the fairing half of a launch vehicle and a device for its implementation |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846246A (en) * | 2020-07-08 | 2020-10-30 | 中北大学 | Portable single reverse-spraying soft landing safety protection device and using method thereof |
| CN111846246B (en) * | 2020-07-08 | 2021-11-09 | 中北大学 | Portable single reverse-spraying soft landing safety protection device and using method thereof |
| CN112429278A (en) * | 2020-11-11 | 2021-03-02 | 陕西中天火箭技术股份有限公司 | Firer ejection recovery mechanism |
| CN112429278B (en) * | 2020-11-11 | 2023-09-15 | 陕西中天火箭技术股份有限公司 | Initiating explosive device ejection recovery mechanism |
| CN112556515A (en) * | 2021-02-19 | 2021-03-26 | 北京星际荣耀空间科技股份有限公司 | Recovery system and method for rocket fairing |
| EP4046912A1 (en) * | 2021-02-19 | 2022-08-24 | Beijing Interstellar Glory Space Technology Co., Ltd. | Recovery system for a rocket fairing and corresponding recovery method |
| CN113022840A (en) * | 2021-04-13 | 2021-06-25 | 中国人民解放军战略支援部队航天工程大学 | Flexible variant airship for recycling fairing of carrier rocket and recycling method |
| RU2792472C1 (en) * | 2022-12-05 | 2023-03-22 | Федеральное государственное автономное образовательное учреждение высшего образования "Омский государственный технический университет" | Method for saving the fairing half of a launch vehicle and a device for its implementation |
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Application publication date: 20191126 |
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