CN107804481A

CN107804481A - Dirigible assist system

Info

Publication number: CN107804481A
Application number: CN201710925993.7A
Authority: CN
Inventors: 廖忠民
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-10-06
Filing date: 2017-10-06
Publication date: 2018-03-16

Abstract

A kind of dirigible assist system, including：Lift emission system；Described lifting emission system, including dirigible combination, launcher；Described dirigible combination, includes the dirigible of more than 2, preferably 3；The locus of described dirigible combination, is the axle centered on the central axis of launcher, into space annular array distribution；By dirigible boosting, aerospace fuel is saved, reduces space flight cost, and mobility is good, can avoid bad climate location, is provided for space launch mission and ensures that window phase is effective, the condition being smoothed out according to schedule；Dirigible assist system mobility is good, is advantageous to the survival ability of raising system, is launched using aerostatic buoyancy transport spacecraft to high-altitude, has saved aerospace fuel, reduced the pollution to environment；Reach and significantly improve efficiency, cost-effective, enhancing environmental protection beneficial effect.

Description

Dirigible assist system

Technical field

The present invention relates to space industry, more particularly to a kind of dirigible assist system.

Background technology

Valuable aerospace fuel is saved, reduction of expenditure is not only contributed to, is also beneficial to environmental protection；What dirigible rising utilized is empty Lift of gas, the consumption energy is very few, and the spacecraft that needs are launched by dirigible first lifts certain altitude, then launches, Ke Yida To the purpose for saving aerospace fuel.

The content of the invention

Therefore, the present invention proposes a kind of dirigible assist system, aerospace fuel is saved with power-assisted, space flight cost is reduced, carries High space flight benefit.

Fig. 1 is a kind of lifting emission system schematic diagram of dirigible assist system, and Fig. 2 is Fig. 1 schematic top plan view, first dirigible 1 is connected with launcher 6 by cable combination 7, and second dirigible 2, the third dirigible 3 are identical with the connection of launcher 6,3 dirigibles The axle centered on the central axis (namely central axis of spacecraft to be launched 5) of launcher 6, into space annular array distribution； A kind of dirigible assist system, including：Control centre, control centre's backup, lifts emission system, safety system；Described Control centre, including central computer control system, power-supply system, central management system, centre information system, centre data system System, dirigible TT＆C system, Spacecraft Launch TT＆C system, communications network system, base, standard frequency system during standard, and be System backup；Described system, including hardware, software；Described management system, including operational procedure；Control centre backs up, and sets There are the back-up device of control centre, described backup, including hardware backup, software backup, data backup；In described control The heart, the position of control centre's backup, including, or in same building thing, or in different buildings, or together In one vehicles, or in the different vehicles；Described lifting emission system, including dirigible combination, launcher；It is described Dirigible combination, include the dirigible of more than 2, preferably 3, in addition to cable combination 7；The space bit of described dirigible combination Put, be the axle centered on the central axis of launcher 6, into space annular array distribution；Described cable combination 7, including machinery Attachment means, electrical connection arrangement；Described electrical connection arrangement includes power connector, information attachment means；Described Dirigible, including control system, air bag, auxiliary balloon, cabin, propulsion plant, helm gear；Described control system, including meter Calculation machine control system, power-supply system, information and information exchange link system, data system, attitude control system, communication network system System, and system backup；Described cabin, including driving cabin, enging cabin or also include crew compartment；

Fig. 3 is the enlarged diagram of launcher 6, and Fig. 4 is Fig. 3 schematic top plan view；Described launcher 6 includes, horizontal Annular girder group 64, vertical support group 62, guide runner 66, guide runner support 63, weight supporting slide 67, weight supporting slide support 61, Horizontal annular beam joint device 65；Described horizontal loops ellbeam group, include the horizontal loops ellbeam of more than 2；Described vertical branch Vertical support more than post group, including 3；Described horizontal loops ellbeam, is a kind of separable ring ellbeam, several horizontal annulars Beam element, by horizontal annular beam joint device, connect into a continuous end to end annular girder；Described horizontal annular Beam joint device, be that one kind electricly connects device, under electroless state, keep connection status, obtain it is electric after, release releases connection；Institute The guide runner stated, controlled by the electric control gear in guide runner support, under electroless state, keep guiding state, obtain it is electric after, release Releasing is put to be oriented to；Described weight supporting slide, controlled by the electric control gear in weight supporting slide support, under electroless state, keep load-bearing State, obtain it is electric after, release release load-bearing；Described launcher also includes sensor, controlling organization, executing agency, with dirigible Mechanical interface, electricity interface, information interface；Described sensor includes, electronic type twin shaft horizon sensor, pressure sensor, Displacement transducer.

The operational procedure of described dirigible assist system includes, and step 1, contact meteorological department, understands plan launch site Launch time accurate weather forecast situation, if launch requirements are met by original plan place prepare launch, if be not inconsistent Closing launch requirements, then alternative weather forecast meets launch requirements, and meets the place transition of transmitter site requirement, prepares transmitting；Step Rapid 2, place cleaning is checked, is checked, detection device, carry out every preparation, all departments are confirmed after meeting regulatory requirements, feedback The information that confirmation receives to control centre, control centre's analyzing and processing, after confirming that each link meets the requirements, sends entrance The instruction of next step；Described inspection, detection device, including, after being connected to the instruction of control centre, staff checks again for Dirigible combines the connection state with launcher, the self-condition of spacecraft, spacecraft and the connection state of lifting emission system, and Information is fed back to control centre in time；Step 3, after being connected to the climb command of control centre, grappling, anchor system are released, release flies Ship and launcher, start safe rising；In uphill process, control centre is monitored to the state for lifting emission system, and root The information obtained according to monitoring sends instruction in good time if necessary, lifts the instruction that emission system mission control center sends, and in time Feedback command implementation status；Lifting emission system monitors spacecraft attitude control system feedack simultaneously, and is arranged on The information of the various sensor feedbacks in emission system is lifted, is handled, voluntarily drafts counter-measure in good time if necessary, is lifted The information of acquisition and the measure drafted are transferred to control centre by system in time；Step 4, when control centre according to itself monitor The monitoring information of system, spacecraft attitude control system feedack, lifting all acquisitions of emission system feedack Validation of information spacecraft has reached predetermined transmitting position, and the state of spacecraft and various external conditions all meet transmitting and wanted When asking, firing command is sent, each system, each link of whole dirigible assist system enter spacecraft ignition operation state；(boat Its device is lighted a fire, and other each systems, the monitoring of each link coordinate)；After step 5, spacecraft igniting start, when pressure sensor, displacement The signal of sensor feedback confirms that spacecraft has been moved off the weight-bearing surface of weight supporting slide, control system control, weight supporting slide branch Electric control gear control weight supporting slide in frame, which discharges, releases load-bearing, and the electric control gear control guide runner in guide runner support is released Releasing is put to be oriented to；Then, the electric control gear control release of horizontal annular beam joint device releases connection, is divided into the transmitting of 3 parts Frame, by Action of Gravity Field, it is each moved to below connected dirigible, Fig. 5 is that launcher 6 flies after decomposing with first after Spacecraft Launch The schematic diagram that the continuous part 68 of ship 1 is moved to below first dirigible；Then, each dirigible carries part launcher respectively to leaving boat Its device and the direction flight for ensuring holding safe distance between each dirigible；In Fig. 2, arrow 20 represents the horizontal component velocity of spacecraft Direction, arrow 21 represent the direction of the horizontal component velocity of first dirigible, and arrow 22 represents the direction of the horizontal component velocity of second dirigible, arrow 23 Represent the direction of the horizontal component velocity of the third dirigible；Step 6, each dirigible carry part launcher and return to control centre appointed place, whole Each system, each link of individual dirigible assist system are checked installations and facilities, safeguarded, maintained, and place is cleared up, examined Look into, safeguard, personnel are checked, carry out safety verification, work summary.

Described safety system, including internal security monitor protective system, perimeter security patrol monitor protective system； Described perimeter security patrol monitor protective system, including flooring-safe patrol monitoring protection subsystem, air security patrol prison Control protection subsystem；Described air security patrol monitoring protection subsystem, including monitoring helicopter, monitoring dirigible, it is described Monitoring helicopter includes manned monitoring helicopter, unmanned monitoring helicopter, and described dirigible includes manned prison Control dirigible, unmanned monitoring dirigible.

The present invention saves aerospace fuel by dirigible boosting, reduces space flight cost, and due to dirigible assist system, machine Dynamic property is good, can avoid bad climate location so that space launch work is not influenceed by bad weather condition, is sent out for space flight The task of penetrating, which provides, ensures that window phase is effective, the condition being smoothed out according to schedule；Dirigible assist system mobility is good, is advantageous to The survival ability of raising system, launched using aerostatic buoyancy transport spacecraft to high-altitude, add the potential energy that takes off of spacecraft, keep away The aerodynamic drag of bottom stiff air has been opened, has saved aerospace fuel, has reduced the pollution to environment；Reach and significantly improve effect Rate, cost-effective, enhancing environmental protection beneficial effect.

Brief description of the drawings

Fig. 1 is a kind of lifting emission system schematic diagram of dirigible assist system.

Fig. 2 is Fig. 1 schematic top plan view.

Fig. 3 is the enlarged diagram of launcher 6.

Fig. 4 is Fig. 3 schematic top plan view.

Fig. 5 is the signal moved partially into below first dirigible that launcher is connected after decomposing with first dirigible after Spacecraft Launch Figure.

Embodiment

Embodiment 1, Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 are also the schematic diagram of embodiment 1, and its each several part forms and what is acted on says It is bright as described in [0004] section, [0005] section, [0006] section；This is good in predetermined launch time, former preselected launching site meteorological condition It is good, meet the requirement of transmitting operational procedure, launched in former preselected launching site；Launch the course of work as described in [0006] section.

Embodiment 2, Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 are also the schematic diagram of embodiment 1, and its each several part forms and what is acted on says It is bright as described in [0004] section, [0005] section；This is that former preselected launching site meteorological condition is bad, does not meet in predetermined launch time Launch the requirement of operational procedure, it is necessary to which alternative weather forecast meets the transition of launch requirements place, preparation transmitting；Therefore need to complete The selection at launching site, complete place of safety and determine.The operational procedure of described dirigible assist system also includes, launching site and place of safety Requirement；The requirement at described launching site and place of safety, including, the region of described launching site and place of safety, including lifting hair The ground anchoring dock area of system is penetrated, to floor projection covering when lifting emission system ascending path and reaching transmitting position Region within the km of region distance 3, the ground and its neighboring area of the estimated flight path covering of spacecraft；Described launching site Selection requirement, including, away from the densely inhabited district such as village, fairground, city；Away from oil depot, power plant, transformer station, warehouse Deng Important building facility；Away from high-intensity magnetic field and shoot high frequency domain；Launch ground and require smooth firm, no combustibles；Selection, determine Behind good new launching site, timely transition, then launched；Launch the course of work as described in [0006] section.

In order to describe the present invention in detail, this specification citing describes some concrete structures and data, and these are all only Various changes, replacement and change institute non-limiting in order to illustrate, being done in the range of the basic thought of the claims in the present invention Caused all or part of equivalent, all within the scope of the invention as claimed.

Claims

1. a kind of dirigible assist system, it is characterized in that, including：Control centre, control centre's backup, lift emission system, safety Protection system；Described control centre, including central computer control system, power-supply system, central management system, central information System, central data system, dirigible TT＆C system, Spacecraft Launch TT＆C system, communications network system, base, standard during standard Frequency system, and system backup；Described system, including hardware, software；Described management system, including operational procedure；Control Center backup processed, it is standby to be provided with the back-up device of control centre, described backup, including hardware backup, software backup, data Part；Described control centre, the position of control centre's backup, including, or in same building thing, or build in different Build in thing, or in the same vehicles, or in the different vehicles；Described lifting emission system, including dirigible Combination, launcher；Described dirigible combination, include the dirigible of more than 2, preferably 3, described lifting emission system, go back Including cable combination；The locus of described dirigible combination, is the axle centered on the central axis of launcher, into space annular Array distribution；Described cable combination, including mechanical connecting device, electrical connection arrangement；Described electrical connection arrangement includes Power connector, information attachment means；Described dirigible, including control system, air bag, auxiliary balloon, cabin, propulsion dress Put, helm gear；Described control system, including computer control system, power-supply system, information and information exchange link system System, data system, attitude control system, communications network system, and system backup；Described cabin, including driving cabin, start Cabin or also include crew compartment.

2. a kind of dirigible assist system according to claim 1, it is characterized in that, described launcher includes, horizontal annular Beam group, vertical support group, guide runner, guide runner support, weight supporting slide, weight supporting slide support, horizontal loops ellbeam connection dress Put；Described horizontal loops ellbeam group, include the horizontal loops ellbeam of more than 2；Described vertical support group, including more than 3 Vertical support；Described horizontal loops ellbeam, it is a kind of separable ring ellbeam, several horizontal annular beam elements, passes through horizontal loops Ellbeam attachment means, connect into a continuous end to end annular girder；Described horizontal annular beam joint device, it is a kind of Electricly connect device, under electroless state, keep connection status, obtain it is electric after, release releases connection；Described guide runner, is led Electric control gear control into slider bracket, under electroless state, keeps guiding state, obtain it is electric after, release, which releases, to be oriented to；Described Weight supporting slide, controlled by the electric control gear in weight supporting slide support, under electroless state, keep weight bearing situations, obtain it is electric after, release solution Except load-bearing；Described launcher also includes sensor, controlling organization, executing agency, mechanical interface, electricity interface with dirigible, Information interface；Described sensor includes, electronic type twin shaft horizon sensor, pressure sensor, displacement transducer.

3. a kind of dirigible assist system according to claim 1, it is characterized in that, the operation rule of described dirigible assist system Journey includes, step 1, contact meteorological department, the accurate weather forecast situation of the launch time of plan launch site is understood, if symbol Close launch requirements then by original plan place prepare transmitting, if launch requirements are not met select else weather forecast meet transmitting will Ask, and meet the place transition of transmitter site requirement, prepare transmitting；Step 2, place cleaning is checked, check, detection device, enter The every preparation of row, all departments are confirmed after meeting regulatory requirements, feedback acknowledgment information to control centre, at control centre's analysis The information received is managed, after confirming that each link meets the requirements, sends the instruction into next step；Described inspection, detection are set It is standby, including, after being connected to the instruction of control centre, staff checks again for dirigible combination and the connection state of launcher, space flight The self-condition of device, spacecraft and the connection state of lifting emission system, and information is fed back to control centre in time；Step 3, After being connected to the climb command of control centre, grappling, anchor system are released, dirigible and launcher is discharged, starts safe rising；Uphill process In, control centre is monitored to the state for lifting emission system, and the information obtained according to monitoring sends finger in good time if necessary Order, the instruction that lifting emission system mission control center sends, and feedback command implementation status in time；Lift emission system simultaneously Monitor spacecraft attitude control system feedack, and the letter of the various sensor feedbacks in lifting emission system Breath, is handled, and voluntarily drafts counter-measure in good time if necessary, and lifting system is timely the information of acquisition and the measure drafted It is transferred to control centre；Step 4, when control centre is according to the monitoring information of itself monitoring system, spacecraft attitude control system Feedack, the validation of information spacecraft of lifting all acquisitions of emission system feedack have reached predetermined transmitting position Put, and when the state of spacecraft and various external conditions all meet launch requirements, send firing command, whole dirigible assist system Each system, each link enter spacecraft ignition operation state；Step 5, spacecraft igniting start after, when pressure sensor, The signal of displacement transducer feedback confirms that spacecraft has been moved off the weight-bearing surface of weight supporting slide, then control system controls, load-bearing Electric control gear control weight supporting slide in slider bracket, which discharges, releases load-bearing, and the electric control gear control in guide runner support is oriented to Sliding block release, which releases, to be oriented to；Then, the electric control gear control release of horizontal annular beam joint device releases connection, is divided into 3 parts Launcher, by Action of Gravity Field, be each moved to below connected dirigible, then, each dirigible carries part launcher difference To leaving spacecraft and ensure to keep between each dirigible the direction of safe distance to fly；Step 6, each dirigible carry part launcher Control centre appointed place is returned to, each system, each link of whole dirigible assist system are checked installations and facilities, tieed up Shield, maintenance, are cleared up place, are checked, are safeguarded, personnel are checked, carry out safety verification, work summary.

4. a kind of dirigible assist system according to claim 1, it is characterized in that, described safety system, including it is interior Portion's safety monitoring protection system, perimeter security patrol monitor protective system；Described perimeter security patrol monitor protective system, bag Include flooring-safe patrol monitoring protection subsystem, air security patrol monitoring protection subsystem；Described air security patrol prison Control protection subsystem, including monitoring helicopter, monitoring dirigible, described monitoring helicopter include it is manned monitoring helicopter, Unmanned monitoring helicopter, described dirigible include manned monitoring dirigible, unmanned monitoring dirigible.

5. a kind of dirigible assist system according to claim 1, it is characterized in that, the operation rule of described dirigible assist system Journey also includes, the requirement of launching site and place of safety；The requirement at described launching site and place of safety, including, described launching site and The region of place of safety, include the ground anchoring dock area of lifting emission system, lift emission system ascending path and reach hair To the region within the km of region distance 3 of floor projection covering, the ground of the estimated flight path covering of spacecraft when penetrating position And its neighboring area；The selection requirement at described launching site, including, away from densely inhabited districts such as village, fairground, cities；Far From the Important building facility such as oil depot, power plant, transformer station, warehouse；Away from high-intensity magnetic field and shoot high frequency domain；Launch ground and require flat It is whole firm, no combustibles.