CN203083454U - Single stage rocket device - Google Patents
Single stage rocket device Download PDFInfo
- Publication number
- CN203083454U CN203083454U CN 201220690684 CN201220690684U CN203083454U CN 203083454 U CN203083454 U CN 203083454U CN 201220690684 CN201220690684 CN 201220690684 CN 201220690684 U CN201220690684 U CN 201220690684U CN 203083454 U CN203083454 U CN 203083454U
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- saltus step
- pressure chamber
- pressure
- liquid storage
- stage rocket
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Abstract
The utility model discloses a single stage rocket device, and belongs to the field of experiment detection air vehicles based on liquid recoil force. The single stage rocket device comprises a liquid storage cabin, an air pressure cabin, a control cabin and a pressure jumping device, wherein the pressure jumping device acts according to pressure in the air pressure cabin. The control cabin is arranged on the top of the air pressure cabin and connected with the air pressure cabin through the pressure jumping device in a detachable mode. The liquid storage cabin is arranged on the bottom of the air pressure cabin, communicated with the air pressure cabin and provided with a jetting opening. Atmospheric pressure is utilized as a driving source of the single stage rocket device, liquid recoil is used as driving force, the driving structure is simplified, and the weight of a rocket body is reduced. In addition, propellant can be the liquid which is low in cost and uninflammable, and therefore operating cost is lowered greatly, and safety is improved.
Description
Technical field
The utility model relates to the capable aircraft of the experimental detection field based on the liquid recoil strength, particularly a kind of one-stage rocket device.
Background technology
Modern rocket is a kind ofly to obtain reaction force by the high velocity jet high-temperature high-pressure fuel gas, and the aircraft that utilizes the reaction force that produces to push ahead.It mainly is made up of the rocket body, propulsion system and the guidance system that connect successively.Wherein, rocket body is an indispensable part in the rocket, and each system of rocket all is installed on it, and its inside accommodates a large amount of propellants.During propellant combustion in the rocket, has very big momentum from the gas of rocket body afterbody ejection, according to the law of conservation of momentum, big reverse momentum such as rocket acquisition, thereby continuous back attack phenomenon takes place, along with the consumption of propellant, the quality of rocket reduces gradually, acceleration constantly increases, and when propellant burnout, rocket promptly flies along predetermined space orbit with the speed that obtains.
Yet there is following problem in modern rocket: the first, and the energy density of fuel is low, need carry a large amount of fuel during emission, thereby has increased the weight of rocket.The second, modern rocket adopts fuel as power source, and the cost height of fuel, and be combustibles, thereby security is low.
The utility model content
In order to solve above-mentioned modern rocket Heavy Weight, cost height and the low problem of security, the utility model embodiment provides a kind of one-stage rocket device.Described technical scheme is as follows:
The utility model embodiment provides a kind of one-stage rocket device, it comprises liquid storage cabin, pressure chamber, control cabinet and the pressure saltus step device that moves according to the pressure in the described pressure chamber, described control cabinet is positioned at the top of described pressure chamber, and described control cabinet is connected by described pressure saltus step device separably with described pressure chamber, described liquid storage freight space is communicated with in the bottom of described pressure chamber and with described liquid storage cabin, and described liquid storage cabin is provided with jet.
Preferably, the top of described pressure chamber is provided with the ventilation interface, described pressure saltus step device comprises structure, the saltus step pin of saltus step air chamber and action along with moving of described saltus step air chamber, offer the cross groove of top seal in the described structure, described ventilation interface stretches in the pod of described cross groove and with described structure fixedlys connected, described saltus step air chamber can be located in the described cross groove movably along described pod, and be provided with elastic reseting part between the top of described saltus step air chamber and described structure, described saltus step air chamber is set in movably on the described ventilation interface and with described ventilation interface and is communicated with, described saltus step pin is located in the translot of described cross groove, the inwall of described control cabinet is provided with locating slot, and the free end of described saltus step pin is plugged in the described locating slot separably.
Further, be provided with one in the described saltus step pin and be sold back to a grain-producing area spring, described two ends of being sold back to a grain-producing area spring are fixed with the inwall of the described translot of described saltus step pin and described cross groove respectively, described saltus step pin and described saltus step air chamber opposing end faces are that inclined-plane and described inclined-plane and described saltus step air chamber lean, and the inclination angle on described inclined-plane is an acute angle.
Further, the angle at described inclination angle is 45 ° ~ 60 °.
Preferably, be arranged with sealing ring on the described intake interface of described pressure chamber, described saltus step air chamber is set on the described sealing ring.
Alternatively, described sealing ring is a rubber ring.
Further, one-stage rocket device of the present utility model also comprises at least two balance wing, and described balance wing edge circumferentially is installed on the described liquid storage cabin equably, on the described pressure chamber or the junction of described liquid storage cabin and described pressure chamber.
Preferably; one-stage rocket device of the present utility model also comprises landing pack, protection assembly and data record assembly; described data record assembly is fixed in the described control cabinet; described protection assembly and described landing pack are located in the described control cabinet, and described landing pack is connected with described protection assembly with described control cabinet.
Alternatively, the liquid in the described liquid storage cabin is water, and the gas pressure intensity in the described pressure chamber is 130PSI.
The beneficial effect that the technical scheme that the utility model embodiment provides is brought is: present embodiment, has been simplified push structure, thereby has been alleviated the weight of rocket body as the promotion source and adopt liquid recoil as motive force with atmospheric pressure.In addition, propellant can be the low and nonflammable liquid of cost, thereby can reduce operating cost greatly and improve security.
Description of drawings
In order to be illustrated more clearly in the technical scheme among the utility model embodiment, the accompanying drawing of required use is done to introduce simply in will describing embodiment below, apparently, accompanying drawing in describing below only is embodiment more of the present utility model, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of the one-stage rocket device that provides among the utility model embodiment;
Fig. 2 is the structural representation that the junction of liquid storage cabin and pressure chamber is provided for the balance wing of the one-stage rocket device that provides among the utility model embodiment;
Fig. 3 is the structural representation for the pressure saltus step device of the one-stage rocket device that provides among the utility model embodiment.
The specific embodiment
For making the purpose of this utility model, technical scheme and advantage clearer, the utility model embodiment is described in further detail below in conjunction with accompanying drawing.
Embodiment
Referring to Fig. 1-2, present embodiment provides a kind of one-stage rocket device, and it comprises liquid storage cabin 10, pressure chamber 11, control cabinet 12 and the pressure saltus step device 15 that moves according to the pressure in the pressure chamber 11.Control cabinet 12 is connected by pressure saltus step device 15 separably with pressure chamber 11, and control cabinet 12 is positioned at the top of pressure chamber 11.Liquid storage cabin 10 is communicated with pressure chamber 11, and liquid storage cabin 10 is positioned at the bottom of pressure chamber 12.The bottom in liquid storage cabin 10 is provided with jet 101.
Particularly, be provided with breather pipe 14 between the top in liquid storage cabin 10 and pressure chamber 11 bottoms, breather pipe 14 two ends are connected with pressure chamber 11 with liquid storage cabin 10 respectively and liquid storage cabin 10, breather pipe 14 and pressure chamber 11 are communicated with successively.The top of pressure chamber 11 is provided with ventilation interface 111.
Further, referring to Fig. 3, the pressure saltus step device 15 of present embodiment comprises structure 151, saltus step air chamber 152 and a pair of saltus step pin 153, and saltus step pin 153 moves along with moving of saltus step air chamber 152.Offer the cross groove 154 of top seal in the structure 151, this cross groove 154 comprises pod 1541 and the translot 1542 vertical with pod 1541, wherein, pod 1541 extends along the length direction of rocket body, and translot 1542 extends along the direction vertical with the length direction of rocket body.The ventilation interface 111 of pressure chamber 11 stretches in the pod 1541 of cross groove 154 and with structure 151 fixedlys connected.Saltus step air chamber 152 can be located in the pod 1541 of cross groove 154 movably along pod 1541, and is provided with elastic reseting part between the top of saltus step air chamber 152 and structure 151, and when in the pressure chamber 11 during gassy, this elastic reseting part is in compressive state.Saltus step air chamber 152 is set in movably on the ventilation interface 111 and with ventilation interface 111 and is communicated with, saltus step pin 153 is located in the translot 1542 of 154 cross grooves, the inwall of control cabinet is provided with locating slot 121, and the free end of saltus step pin 153 is plugged in the locating slot 121 separably.
Particularly, in the present embodiment, be arranged with sealing ring 112 on the ventilation interface 111 of pressure chamber 11, saltus step air chamber 152 is set on the sealing ring 112 of ventilation interface 111, and sealing ring 112 is preferably rubber ring.
Further, in the present embodiment, saltus step air chamber 152 is downward opening tubular structure, and the outer wall at saltus step air chamber 152 tops is provided with projection 1521, and elastic reseting part is back an axle spring 1522.An end that returns axle spring 1522 is sheathed on the projection 1521 at saltus step air chamber 152 tops and with saltus step air chamber 152 and offsets, return the other end of axle spring 1522 and cross groove 154 pod 1541 roof against, thereby saltus step air chamber 152 telescopically elasticity are connected in the pod 1541 of cross groove 154.
Further, a pair of saltus step pin 153 symmetrically telescopically elasticity be located in the translot 1542 of cross groove 154 of structure 151 and and contact separably with the both sides of saltus step air chamber 152.The inside of each saltus step pin 153 offers the through hole 1531 that radially connects along saltus step pin 153, one is sold back to a grain-producing area spring 1532 is located in the through hole 1531 and an end of being sold back to a grain-producing area spring 1532 is fixed on the inwall of through hole 1531 of saltus step pin 153, being sold back to a grain-producing area the inwall of the translot 1542 of the other end of spring 1532 and cross groove 154 fixes, locating slot 121 on the free end of saltus step pin 153 and pressure chamber 11 inwalls over against, thereby saltus step pin 153 telescopicallies are plugged in the locating slot 121 of pressure chamber 11.Further, saltus step pin 153 is the inclined-plane with saltus step air chamber 152 opposing end faces, and this inclined-plane and saltus step air chamber 152 lean, and the inclined angle alpha on this inclined-plane is acute angle, and preferably, inclined angle alpha is 45 ° ~ 60 °.Know that easily saltus step pin 153 also can be arcwall face with saltus step air chamber 152 opposing end faces.
Need to prove, in the present embodiment, saltus step air chamber 112 is a tubular structure, the end face of saltus step pin 153 is the inclined-plane, but not as limit, in other embodiments, the end face of saltus step pin 153 also can be vertical plane, and the vertical plane of the tapered or corresponding saltus step pin in the top of saltus step air chamber is provided with inclined-plane or arcwall face.
Further, rocket body comprises that also 13, three balance wing 13 of three balance wing are installed on the outer wall in liquid storage cabin 10 equably along the circumferential of liquid storage cabin 10, and particularly, the central angle θ between per two adjacent balance wing 13 is 120 °.Need to prove that the quantity of balance wing can be provided with according to actual needs.
Further, be fixed with data record assembly (not shown) and landing pack 122 in the control cabinet 12, landing pack 122 is connected with control cabinet 12 by rope.Like this, after pressure chamber 11 and control cabinet 12 disengagings, landing pack 122 can be opened, and guarantees that data record assembly (not shown) steadily falls, and is not damaged.Data record assembly (not shown) is made of circuit, camera, temperature sensor and light intensity sensor etc., has data recording function, can write down all flying qualities, so that make the experiment feedback.
The course of work of the one-stage rocket device in the present embodiment is: the jet 101 by 10 bottoms, liquid storage cabin injects liquid in liquid storage cabin 10 earlier, and present embodiment adopts water as injecting liquid; Then, adopting air compressor is the gas of 130PSI by jet 101 injecting gas pressure in pressure chamber 11 of 10 bottoms, liquid storage cabin, thereby is pressure chamber 11 superchargings.Then, open the emission system of rocket body, after rocket body breaks away from launcher, be subjected to the recoil strength of jet 101, rocket body is risen straight up, after the injection of the liquid in the liquid storage cabin 10 finishes, the very fast release of air pressure in the pressure chamber 11, make rocket body lose power source, simultaneously, because the pressure in the pressure chamber 11 is kept to standard atmospheric pressure, the a pair of saltus step pin 153 of pressure saltus step device 15 becomes contraction state, liquid storage cabin 10 and pressure chamber 11 break away from, and the landing pack 122 in the control cabinet 12 freely is scattered and opens, and can land stably by the control cabinet 12 that rope is connected with landing pack 122.
The utility model embodiment has simplified push structure, thereby has alleviated the weight of rocket body by utilizing atmospheric pressure as the promotion source and adopt liquid recoil as motive force.In addition, the propellant in the rocket body can be the low and nonflammable liquid of cost, thereby can reduce operating cost greatly and improve security.
The above only is preferred embodiment of the present utility model, and is in order to restriction the utility model, not all within spirit of the present utility model and principle, any modification of being done, is equal to replacement, improvement etc., all should be included within the protection domain of the present utility model.
Claims (9)
1. one-stage rocket device, it is characterized in that, comprise liquid storage cabin, pressure chamber, control cabinet and the pressure saltus step device that moves according to the pressure in the described pressure chamber, described control cabinet is positioned at the top of described pressure chamber, and described control cabinet is connected by described pressure saltus step device separably with described pressure chamber, described liquid storage freight space is communicated with in the bottom of described pressure chamber and with described liquid storage cabin, and described liquid storage cabin is provided with jet.
2. one-stage rocket device as claimed in claim 1, it is characterized in that, the top of described pressure chamber is provided with the ventilation interface, described pressure saltus step device comprises structure, the saltus step pin of saltus step air chamber and action along with moving of described saltus step air chamber, offer the cross groove of top seal in the described structure, described ventilation interface stretches in the pod of described cross groove and with described structure fixedlys connected, described saltus step air chamber can be located in the described cross groove movably along described pod, and be provided with elastic reseting part between the top of described saltus step air chamber and described structure, described saltus step air chamber is set in movably on the described ventilation interface and with described ventilation interface and is communicated with, described saltus step pin is located in the translot of described cross groove, the inwall of described control cabinet is provided with locating slot, and the free end of described saltus step pin is plugged in the described locating slot separably.
3. one-stage rocket device as claimed in claim 2, it is characterized in that, be provided with one in the described saltus step pin and be sold back to a grain-producing area spring, described two ends of being sold back to a grain-producing area spring are fixed with the inwall of the described translot of described saltus step pin and described cross groove respectively, described saltus step pin and described saltus step air chamber opposing end faces are that inclined-plane and described inclined-plane and described saltus step air chamber lean, and the inclination angle on described inclined-plane is an acute angle.
4. one-stage rocket device as claimed in claim 3 is characterized in that, the angle at described inclination angle is 45 °～60 °.
5. as each described one-stage rocket device of claim 2-4, it is characterized in that be arranged with sealing ring on the described ventilation interface of described pressure chamber, described saltus step air chamber is set on the described sealing ring.
6. one-stage rocket device as claimed in claim 5 is characterized in that, described sealing ring is a rubber ring.
7. as each described one-stage rocket device of claim 2-4, it is characterized in that, described rocket body also comprises at least two balance wing, described balance wing along described rocket body circumferentially be installed on the described liquid storage cabin equably, on the described pressure chamber or the junction of described liquid storage cabin and described pressure chamber.
8. as each described one-stage rocket device of claim 2-4, it is characterized in that, described rocket body also comprises landing pack and data record assembly, described data record assembly is fixed in the described control cabinet, described landing pack is located in the described control cabinet, and described landing pack is connected with described control cabinet.
9. as each described one-stage rocket device of claim 2-4, it is characterized in that the liquid in the described liquid storage cabin is water, the gas pressure intensity in the described pressure chamber is 130PSI.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220690684 CN203083454U (en) | 2012-12-12 | 2012-12-12 | Single stage rocket device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220690684 CN203083454U (en) | 2012-12-12 | 2012-12-12 | Single stage rocket device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203083454U true CN203083454U (en) | 2013-07-24 |
Family
ID=48829281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220690684 Withdrawn - After Issue CN203083454U (en) | 2012-12-12 | 2012-12-12 | Single stage rocket device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203083454U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033097A (en) * | 2012-12-12 | 2013-04-10 | 江汉大学 | Liquid backflushing single-stage rocket body |
-
2012
- 2012-12-12 CN CN 201220690684 patent/CN203083454U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033097A (en) * | 2012-12-12 | 2013-04-10 | 江汉大学 | Liquid backflushing single-stage rocket body |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130724 Effective date of abandoning: 20141029 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20130724 Effective date of abandoning: 20141029 |
|
| RGAV | Abandon patent right to avoid regrant |