CN108592711B - Recyclable combined structure at tail end of carrier rocket - Google Patents
Recyclable combined structure at tail end of carrier rocket Download PDFInfo
- Publication number
- CN108592711B CN108592711B CN201810317082.0A CN201810317082A CN108592711B CN 108592711 B CN108592711 B CN 108592711B CN 201810317082 A CN201810317082 A CN 201810317082A CN 108592711 B CN108592711 B CN 108592711B
- Authority
- CN
- China
- Prior art keywords
- semi
- tail end
- runway
- cylindrical
- cylindrical rocket
- 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.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/08—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles for carrying measuring instruments; Arrangements for mounting sensitive cargo within a projectile; Arrangements for acoustic sensitive cargo within a projectile
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Hall/Mr Elements (AREA)
Abstract
The invention discloses a recyclable combined structure of a carrier rocket tail end, which comprises a cylindrical rocket tail end and a recycling runway, wherein the cylindrical rocket tail end is composed of two semi-cylindrical rocket tail ends, the two semi-cylindrical rocket tail ends are mutually spliced through plane ends of the two semi-cylindrical rocket tail ends, an electromagnetic circuit is arranged on the plane end of each semi-cylindrical rocket tail end, a controller and a power supply connected with the controller are arranged in each semi-cylindrical rocket tail end, and the power supply is connected with the electromagnetic circuit. The invention divides the tail end rocket into two parts, the small satellites are respectively arranged in the tail ends of the semi-cylindrical rockets, and the tail end of each semi-cylindrical rocket can independently fly according to the orbit and release the internal satellite, thereby solving the problems of large flight burden and control difficulty of the traditional tail end rocket. The acting force between the two semi-cylindrical rocket ends is changed through the magnetic fields generated by the respective electromagnetic circuits, polymerization and separation can be carried out repeatedly, the structure is simple, the control stability is high, and the development of aerospace industry is promoted.
Description
Technical Field
The invention relates to the technical field of space rockets, in particular to a recyclable combined structure at the tail end of a carrier rocket.
Background
With the development of electronic technology, electronic products are increasingly miniaturized and have increasingly powerful functions. In the field of aerospace, satellites are no exception, and the miniaturization of the satellites promotes the development of a one-arrow-multi-satellite launching technology.
In the traditional one-rocket-multi-satellite launching, satellites are connected in series in a rocket tail end cabin and released when a tail end rocket reaches a preset orbit. However, as the number of satellites increases and the orbit deviates further, the flight burden is increased for the end rocket, and the flight control of the large end rocket is also more difficult.
Disclosure of Invention
The invention aims to solve the technical problem of providing a recyclable and reusable combined structure at the tail end of a carrier rocket, which divides a tail end rocket into two parts, solves the problems of high flight burden and control difficulty of the traditional tail end rocket, and realizes the reuse of the tail end of the rocket.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the tail end of the carrier rocket can be recycled and reused, and the combined structure comprises a cylindrical rocket tail end and a recycling runway, wherein the cylindrical rocket tail end is composed of two semi-cylindrical rocket tail ends, the two semi-cylindrical rocket tail ends are mutually spliced through self plane ends, an electromagnetic circuit is arranged on the plane end of each semi-cylindrical rocket tail end, a controller and a power supply connected with the controller are arranged in each semi-cylindrical rocket tail end, and the power supply is connected with the electromagnetic circuit and used for supplying current to enable the electromagnetic circuit to generate a magnetic field.
The interior of the tail end of the semi-cylindrical rocket is of a hollow structure, the plane end of the tail end of the semi-cylindrical rocket is divided into two oppositely-opened hatches, the hatches are respectively connected to the edge of the tail end of the semi-cylindrical rocket through electric hinges, and the electric hinges are connected with a controller;
the number of the electromagnetic circuits is two, and one electromagnetic circuit is arranged on each hatch cover.
In a further improvement, the electromagnetic circuit comprises at least two solenoids connected in series, and a core disposed within each solenoid.
The recovery runway is further improved in that the recovery runway comprises a runway body, a runway electromagnetic circuit arranged on the runway body, a runway power supply connected with the runway electromagnetic circuit, and a runway controller connected with the runway power supply.
The further improvement is that the hatch cover consists of a triangular cover and a rectangular cover, and the triangular cover and the rectangular cover are respectively connected to the edge of the tail end of the semi-cylindrical rocket through independent electric hinges.
The invention has the beneficial effects that: the tail-end rocket is divided into two parts, the small satellites are respectively arranged in the tail ends of the semi-cylindrical rockets, and the tail end of each semi-cylindrical rocket is independently provided with a driving and controlling device which can independently fly according to the orbit and release the internal satellite, so that the problems of flight burden and large control difficulty of the traditional tail-end rocket are solved. In addition, the acting force between the two semi-cylindrical rocket tail ends is changed through the magnetic field generated by the respective electromagnetic circuit, so that polymerization and separation can be repeatedly carried out, and multiple recycling is realized. And the structure is simple, the control stability is high, the cost is low, and the development of aerospace industry is promoted.
Drawings
FIG. 1 is a schematic view of a barrel rocket tip;
FIG. 2 is a schematic view of a barrel rocket with the end of the barrel rocket in half;
FIGS. 3 and 4 are schematic structural diagrams of two half-cylindrical rocket tail ends after hatch covers are opened respectively;
FIG. 5 is a control schematic of the present invention;
FIG. 6 is a diagram of the entire launch process of the launch vehicle;
FIG. 7 is a schematic view of the configuration of a reclamation runway;
FIG. 8 is a schematic view of a descent recovery process of a semi-cylindrical rocket tip;
the system comprises a cylindrical rocket tail end 1, a semi-cylindrical rocket tail end 100, an electromagnetic circuit 2, a controller 3, a power supply 4, a cabin cover 5, a recovery runway 6, a runway body 601 and a runway electromagnetic circuit 602.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 1 to 5, the reusable combination structure of the launch vehicle end comprises a cylindrical rocket end 1: the cylindrical rocket tail end 1 is composed of two semi-cylindrical rocket tail ends 100, the two semi-cylindrical rocket tail ends 100 are spliced with each other through own plane ends, an electromagnetic circuit 2 is arranged on the plane end of each semi-cylindrical rocket tail end 100, a controller 3 and a power supply 4 connected with the controller 3 are arranged in each semi-cylindrical rocket tail end 100, and the power supply 4 is connected with the electromagnetic circuit 2 and used for supplying current to enable the electromagnetic circuit 2 to generate a magnetic field.
Specifically, the electromagnetic circuit 2 includes at least two solenoids connected in series, and a core disposed in each solenoid, and the solenoid portion with the core built therein generates a magnetic field after being energized, the direction of the magnetic field is controlled by the direction of the current, and the direction of the current supplied from the power source 4 is controlled by the controller 3. The controllers 3 in the two semi-cylindrical rocket tail ends 100 respectively control the electromagnetic circuits 2 on the plane ends of the two semi-cylindrical rocket tail ends, and when the directions of the magnetic fields generated by the electromagnetic circuits 2 on the two plane ends are opposite (the N pole of one magnetic field faces outwards, and the other S pole faces outwards), the two semi-cylindrical rocket tail ends 100 generate a mutual attraction force to keep the rocket tail ends as a whole; when the directions of the magnetic fields generated by the electromagnetic circuits 2 on the two plane ends are the same (for example, the N poles face outwards or the S poles face outwards), a mutual repulsive force is generated between the two half-cylindrical rocket ends 100, the two half-cylindrical rocket ends 100 are separated from each other, and the rocket ends are divided into two parts and independently run.
Moreover, the interior of the semi-cylindrical rocket tail end 100 is of a hollow structure, the plane end of the semi-cylindrical rocket tail end 100 is divided into two hatches 5 which are designed in a half-open mode, the hatches 5 are respectively connected to the edge of the semi-cylindrical rocket tail end 100 through electric hinges (not shown in the figure), the electric hinges are connected with the controller 3, and the controller 3 controls the electric hinges to realize the on-off control of the two hatches 5; there are two electromagnetic circuits 2, one on each hatch 5.
In addition, each hatch 5 is composed of a triangular cover and a rectangular cover, and the triangular cover and the rectangular cover are respectively connected to the edge of the semi-cylindrical rocket end 100 through independent electric hinges. Thus, the total four cover bodies are turned into four flying wings after being rotated and opened, and each flying wing can independently adjust and swing under the control of the controller 3, so that the gliding and landing of the semi-cylindrical rocket tail end 100 and the adjustment of the air attitude are realized.
As shown in fig. 6, a typical launch vehicle includes a primary booster and a secondary booster, as well as a rocket tip at the top end, with a small satellite placed in series within the rocket tip. When the carrier rocket is launched, the first-stage booster works until the fuel is exhausted, and the booster is separated and falls off; then the secondary booster works until the fuel is exhausted, and the secondary booster separates and falls off; the cylindrical rocket tail ends 1 are left, then the controller 3 in one semi-cylindrical rocket tail end 100 controls and changes the current direction, so that the direction of the magnetic field generated by the electromagnetic circuit 2 is changed, the original mutually attractive force is changed into mutual repulsion, and the two semi-cylindrical rocket tail ends 100 are separated from each other and independently run; and then the electric hinge can be controlled to rotate after the rocket reaches a specified position, the two hatches 5 are opened, the internal small satellites are released, and the tail end 100 of the semi-cylindrical rocket falls off.
As shown in fig. 7, the reusable combination structure of the launch vehicle end further includes a recovery runway 6: the recovery runway 6 includes a runway body 601, a runway electromagnetic circuit 602 disposed on the runway body 601, a runway power supply (not shown) connected to the runway electromagnetic circuit 602 (located inside the runway body 601), and a runway controller (located inside the runway body 601, not shown) connected to the runway power supply.
The runway body 601 is ship-shaped and stops at a certain depth below the water surface when working. The runway body 601 is composed of a plurality of runway monomers side by side, and through connecting piece swing joint between the adjacent runway monomers, the runway monomer uses the connecting piece (can be for electronic hinge) to rotate along the horizontal plane as the axle, all is equipped with runway electromagnetic circuit 602 on the free top of every runway, still is equipped with the drive arrangement (can be for the permanent-magnet machine propeller) that is used for providing power for the runway monomer in the free inside of every runway.
As shown in fig. 8, the half-cylindrical rocket tip 100 may be dropped and recovered through the recovery runway 6 after dropping. Firstly, the recovery runway 6 is driven to a designated position, then the runway controller controls a runway power supply to enable the upper part of the recovery runway and the lower part of the semi-cylindrical rocket tail end 100 to form a same-name magnetic pole, mutual repulsion force is generated to reduce the descending speed of the semi-cylindrical rocket tail end 100, the collision between the semi-cylindrical rocket tail end 100 and the water surface is slowed down, when the semi-cylindrical rocket tail end 100 falls to the water surface and slides forwards, the current direction provided by the runway power supply is changed to enable the upper part of the recovery runway 6 and the lower part of the semi-cylindrical rocket tail end 100 to form a different-name magnetic pole, mutual attraction force is generated, therefore, the friction force between the semi-cylindrical rocket tail end 100 and the water surface is increased, the. The two separated and recovered semi-cylindrical rocket tail ends 100 can be reunited by magnetic force to form a complete rocket tail end, so that the reutilization is realized.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (2)
1. The recyclable combined structure at the tail end of the carrier rocket is characterized in that: the device comprises a cylindrical rocket tail end (1) and a recovery runway (6), wherein the cylindrical rocket tail end (1) consists of two semi-cylindrical rocket tail ends (100), the two semi-cylindrical rocket tail ends (100) are spliced with each other through the plane ends of the two semi-cylindrical rocket tail ends, an electromagnetic circuit (2) is arranged on the plane end of each semi-cylindrical rocket tail end (100), a controller (3) and a power supply (4) connected with the controller (3) are arranged in each semi-cylindrical rocket tail end (100), and the power supply (4) is connected with the electromagnetic circuit (2) and used for supplying current to enable the electromagnetic circuit (2) to generate a magnetic field;
the interior of the semi-cylindrical rocket tail end (100) is of a hollow structure, the plane end of the semi-cylindrical rocket tail end (100) is divided into two oppositely-opened hatches (5), the hatches (5) are respectively connected to the edge of the semi-cylindrical rocket tail end (100) through electric hinges, and the electric hinges are connected with the controller (3); the electromagnetic circuit (2) is provided with two electromagnetic circuits, one electromagnetic circuit is arranged on each hatch cover (5), and each electromagnetic circuit (2) comprises at least two series-connected spiral coils and an iron core arranged in each spiral coil;
the recovery runway (6) comprises a runway body (601), a runway electromagnetic circuit (602) arranged on the runway body (601), a runway power supply connected with the runway electromagnetic circuit (602), and a runway controller connected with the runway power supply;
after the tail end (100) of the semi-cylindrical rocket falls off, the semi-cylindrical rocket descends and is recovered through a recovery runway (6), firstly, the recovery runway (6) is driven to a designated position on water, then the runway controller controls the runway power supply to form like magnetic poles above the recovery runway (6) and below the semi-cylindrical rocket tail end (100) to generate mutual repulsive force, reduce the descending speed of the semi-cylindrical rocket tail end (100) and slow down the collision between the semi-cylindrical rocket tail end (100) and the water surface, when the semi-cylindrical rocket tail end (100) falls to the water surface and slides forwards, the current direction provided by the runway power supply is changed, so that the upper part of the recovery runway (6) and the lower part of the semi-cylindrical rocket tail end (100) form unlike magnetic poles to generate mutual attraction, thereby increasing the friction force between the semi-cylindrical rocket tail end (100) and the water surface, shortening the sliding distance of the semi-cylindrical rocket tail end (100) and realizing safe landing.
2. The launch vehicle end reusable composite structure of claim 1 wherein: the hatch cover (5) consists of a triangular cover and a rectangular cover, and the triangular cover and the rectangular cover are respectively connected to the edge of the semi-cylindrical rocket tail end (100) through independent electric hinges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810317082.0A CN108592711B (en) | 2018-04-10 | 2018-04-10 | Recyclable combined structure at tail end of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810317082.0A CN108592711B (en) | 2018-04-10 | 2018-04-10 | Recyclable combined structure at tail end of carrier rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108592711A CN108592711A (en) | 2018-09-28 |
| CN108592711B true CN108592711B (en) | 2021-05-07 |
Family
ID=63621746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810317082.0A Active CN108592711B (en) | 2018-04-10 | 2018-04-10 | Recyclable combined structure at tail end of carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108592711B (en) |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063006B (en) * | 2017-04-03 | 2018-11-27 | 湖北航天技术研究院总体设计所 | A kind of reusable carrying space system and round-trip method |
| CN107554824A (en) * | 2017-09-19 | 2018-01-09 | 谢天立 | A kind of electromagnetic type one-level, booster-missile combination retracting device and method |
-
2018
- 2018-04-10 CN CN201810317082.0A patent/CN108592711B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108592711A (en) | 2018-09-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10982926B2 (en) | Electromagnetic launcher with spiral guideway | |
| US10218251B2 (en) | Electromagnetic launcher with circular guideway | |
| US10370082B2 (en) | Aircraft capable of vertical take-off and landing, vertical and horizontal flight and on-air energy generation | |
| JP4742038B2 (en) | Electromagnetic missile launcher | |
| CN108016603B (en) | Rotor sequencing for dual rotor aircraft | |
| US4817494A (en) | Magnetic reconnection launcher | |
| KR20150089970A (en) | Amphibious flying car | |
| CN106956555A (en) | The empty dual-purpose variant of water based on the conformal semi-ring wing crosses over ROV | |
| CN206813327U (en) | Rotary-type electromagnetic launch device is buried in one kind | |
| CN108592711B (en) | Recyclable combined structure at tail end of carrier rocket | |
| KR101668639B1 (en) | Flight System of mother-baby unmanned aerial vehicle using magnetic force | |
| CN102777342A (en) | Vector magnetic nozzle used for electric propulsion | |
| US7121506B2 (en) | Remotely controlled model airplane having deflectable centrally biased control surface | |
| CN110406688B (en) | Magnetic suspension electromagnetic propulsion integrated carrying sledge for accelerating aircraft | |
| CN113212782B (en) | Ultrashort-distance landing system of fixed-wing unmanned aerial vehicle | |
| CN110615114A (en) | Method and device for assisting landing and landing of airplane | |
| US5222689A (en) | Aircraft having magnetic suspension systems | |
| CN209341956U (en) | A kind of 3D printing folding wing scout missile | |
| CN110406386B (en) | Mechanical guide device for magnetic suspension sledge and magnetic suspension sledge with mechanical guide device | |
| US20050077433A1 (en) | Apparatus and method for maneuvering objects in low/zero gravity environments | |
| CN106347677B (en) | A kind of unmanned machine parachute | |
| CN109878753B (en) | Magnetic suspension boosting and capturing device for aircraft | |
| CN110282160A (en) | Tubaeform electromagnetic type rocket landing recyclable device | |
| CN110525654A (en) | A kind of delivery device of unmanned plane | |
| US11597531B2 (en) | Magnetic refueling boom positioning |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |