CN203083453U - Two-stage boosting type rocket device - Google Patents
Two-stage boosting type rocket device Download PDFInfo
- Publication number
- CN203083453U CN203083453U CN 201220689425 CN201220689425U CN203083453U CN 203083453 U CN203083453 U CN 203083453U CN 201220689425 CN201220689425 CN 201220689425 CN 201220689425 U CN201220689425 U CN 201220689425U CN 203083453 U CN203083453 U CN 203083453U
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- main
- rocket
- saltus step
- liquid storage
- pressure chamber
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Abstract
The utility model discloses a two-stage boosting type rocket device and belongs to the field of experiment exploratory air vehicles based on liquid recoil force. The two-stage boosting type rocket device comprises a main rocket body and at least one secondary rocket body connected with the main rocket body in a detachable mode, wherein the main rocket body comprises a main liquid storage cabin, a main air pressure cabin, a control cabin and a pressure jump device moving according to the pressure in the main air pressure cabin, the control cabin is located on the top of the main air pressure cabin and is connected with the main air pressure cabin in a detachable mode through the pressure jump device, the main liquid storage cabin is located on the bottom of the main air pressure cabin and is communicated with the main air pressure cabin, and a main jet orifice is formed in the bottom of the main liquid storage cabin. According to the two-stage boosting type rocket device, atmospheric pressure is used as a boosting source, the liquid recoil force is used as boosting force, the boosting structure is simplified, the weight of a rocket body is reduced, and rising height of the rocket is increased due to the additional arrangement of the secondary rocket bodies on the main rocket body.
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 twin-stage assisted rocket means.
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 the rocket fuel burning, 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 twin-stage assisted rocket means.Described technical scheme is as follows:
The utility model embodiment provides a kind of twin-stage assisted rocket means, this device comprises the booster-missile combination body that main rocket body and at least one and described main rocket body are connected separably, described main rocket body comprises main liquid storage cabin, main pressure chamber, control cabinet and the pressure saltus step device that moves according to the pressure in the described main pressure chamber, described control cabinet is positioned at the top of described main pressure chamber, and described control cabinet is connected by described pressure saltus step device separably with described main pressure chamber, and described main liquid storage freight space is communicated with in the bottom of described main pressure chamber and with described main liquid storage cabin.
Preferably, be fixed with the collar on the described main rocket body, be fixed with connector on the described booster-missile combination body, described connector is sheathed in the described collar.
Preferably, described connector comprises fixed part and the Plug Division that upwards is bent to form along fixed part, and described fixed part and described booster-missile combination body are fixed, and described Plug Division can be sheathed in the described collar of described main rocket body up or down.
Preferably, described booster-missile combination body comprises secondary liquid storage cabin and the secondary pressure chamber that is communicated with described secondary liquid storage cabin, and described secondary liquid storage bilge portion is provided with the two-stage injection mouth, and described connector is fixed on the described secondary pressure chamber.
Preferably, be provided with the secondary breather pipe between described secondary liquid storage cabin and the described secondary pressure chamber, described secondary liquid storage cabin, described secondary breather pipe and described secondary pressure chamber are communicated with.
Preferably, be provided with main breather pipe between described main liquid storage cabin and the described main pressure chamber, described main liquid storage cabin, described main breather pipe and described main pressure chamber are communicated with.
Preferably, the top of the described main pressure chamber of described main rocket body 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 of described pressure chamber and with described ventilation interface and is communicated with, the described relatively ventilation interface of described saltus step air chamber telescopically elasticity is connected in the described pod of described cross groove, 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 of described control cabinet separably.
Preferably, 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.
Preferably, the main pressure chamber that described main rocket body comprises main liquid storage cabin, be communicated with described main liquid storage cabin, control cabinet and at least two balance wing of being connected separably with described main pressure chamber, described balance wing along described main rocket body circumferentially be installed on the described main liquid storage cabin equably, on the described main pressure chamber or the junction of described main liquid storage cabin and described main pressure chamber, the bottom in described main liquid storage cabin is provided with the main jet loophole, and the described collar is fixed on the described main pressure chamber.
Preferably; described main rocket body 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.
The beneficial effect that the technical scheme that the utility model embodiment provides is brought is: the first, and 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; The second, propellant can be the low and nonflammable liquid of cost, thereby can reduce operating cost greatly and improve security; The 3rd, present embodiment is by setting up the booster-missile combination body on main rocket body, after described booster-missile combination body can break away from main rocket body in main rocket body rising a period of time of assistance and because of depleted of energy, main rocket body still has energy to continue to utilize liquid propulsive thrust to move upward, thereby increased the lifting height of rocket, expanded the range of application of rocket of the present utility model.
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 twin-stage assisted rocket means that provides among the utility model embodiment;
Fig. 2 is the partial enlarged drawing of A part among Fig. 1;
Fig. 3 is the structural representation of the connector of the twin-stage assisted rocket means that provides among the utility model embodiment;
Fig. 4 is the structural representation that the balance wing of the twin-stage assisted rocket means that provides among the utility model embodiment is arranged in the junction of main liquid storage cabin and main pressure chamber.
Fig. 5 is the structural representation of the pressure saltus step device of the twin-stage assisted rocket means 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. 1-4, present embodiment provides a kind of twin-stage assisted rocket means, this device comprise main rocket body with three along the booster-missile combination body that is connected separably on the main rocket body of circumferentially being evenly arranged in of main rocket body and with described main rocket body.Main rocket body comprises main liquid storage cabin 10, main pressure chamber 11, control cabinet 12 and the pressure saltus step device 15 that moves according to the pressure in the main pressure chamber 11.Control cabinet 12 is connected by pressure saltus step device 15 separably with main pressure chamber 11, and control cabinet 12 is positioned at the top of main pressure chamber 11.Main liquid storage cabin 10 is communicated with main pressure chamber 11, and main liquid storage cabin 10 is positioned at the bottom of pressure chamber 12.The bottom in main liquid storage cabin 10 is provided with main jet loophole 101.
Further, be fixed with the collar 30 on the main pressure chamber 11 of main rocket body, the axial line of the collar 30 is parallel with the axis of main rocket body.Each booster-missile combination body comprises secondary liquid storage cabin 20, secondary pressure chamber 21 and is located at secondary breather pipe 22 between secondary liquid storage cabin 20 and the secondary pressure chamber 21.And secondary liquid storage cabin 20, secondary breather pipe 22 and secondary pressure chamber 21 are communicated with successively.The bottom in secondary liquid storage cabin 20 is provided with two-stage injection mouth 201, is fixed with connector 31 on the secondary pressure chamber 21.Described connector 31 specifically comprises fixed part 311 and the Plug Division 312 that upwards is bent to form by fixed part 311.The Plug Division 312 of the connector 31 on the secondary pressure chamber 21 is sheathed in the collar 30 on the main pressure chamber 11 of main rocket body and can moves up and down in the collar 30.
Understandably, the collar 30 also can be fixed on the main liquid storage cabin 10 or main pressure chamber 11 and main liquid storage cabin 10 on each fixes a collar 30.Connector 31 also can be fixed on the secondary liquid storage cabin 20 and be socketed in the collar 30 on the main liquid storage cabin 10 with main rocket body or each is fixed a connector 31 and is socketed in respectively on the main liquid storage cabin 10 and the collar 30 on the main pressure chamber 11 of main rocket body on secondary pressure chamber 21 and the secondary liquid storage cabin 20.
Further, the top of the main pressure chamber 11 of main rocket body is provided with ventilation interface 111.Referring to Fig. 5, the pressure saltus step device 15 of the main rocket body 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 at pressure chamber 11 tops 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.
A pair of further saltus step pin 153 telescopically elasticity symmetrically is located in the translot 1542 of cross groove 154 of structure 151 and with the both sides of saltus step air chamber 152 and is contacted separably.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, with reference to figure 4, main rocket body also comprises three balance wing 13.Particularly, three balance wing 13 are provided with a balance wing 13 between the junction that circumferentially is installed in main liquid storage cabin 10 and main pressure chamber 11 equably of main rocket body and adjacent two booster-missile combination bodies.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 provided with main breather pipe 14 between the top in main liquid storage cabin 10 and main pressure chamber 11 bottoms, the other branch in main breather pipe 14 two ends is connected with main pressure chamber 11 with main liquid storage cabin 10 and main liquid storage cabin 10, main breather pipe 14 and main pressure chamber 11 are communicated with successively.
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 main 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 twin-stage assisted rocket means in the present embodiment is: the main jet loophole 101 by 10 bottoms, main liquid storage cabin injects liquid in main liquid storage cabin 10 earlier, two-stage injection mouth 201 by 20 bottoms, secondary liquid storage cabin injects liquid in secondary liquid storage cabin 20 simultaneously, and present embodiment adopts water as injecting liquid; Then, adopting air compressor is the gas of 130PSI by main jet loophole 101 injecting gas pressure in main pressure chamber 11 of 10 bottoms, main liquid storage cabin, thereby be main pressure chamber 11 superchargings, adopting air compressor simultaneously is the gas of 130PSI by two-stage injection mouth 201 injecting gas pressure in secondary pressure chamber 21 of 20 bottoms, secondary liquid storage cabin.Then, open the emission system of rocket body, after rocket body breaks away from launcher, main rocket body is subjected to the recoil strength of main jet loophole 101 and the recoil strength that the booster-missile combination body is subjected to two-stage injection mouth 201, whole rocket body is risen straight up, at whole rocket flight after a period of time, water in the booster-missile combination body takes the lead in spraying and finishes, because the booster-missile combination body is to be connected with connector 31 by the collar 30 with the main body rocket, under the acting in conjunction of air drag and gravity, a plurality of booster-missile combination bodies downwards and break away from main rocket body, at this moment, because main rocket body has the sustained firing ability of long period, after a plurality of booster-missile combination bodies break away from, main rocket body still continues to quicken to rise, and main rocket body continues to rise.After the injection of the liquid in the main liquid storage cabin 10 finishes; the very fast release of air pressure in the main pressure chamber 11; make main rocket body lose power source; simultaneously; because the pressure in the main pressure chamber 11 is kept to standard atmospheric pressure, a pair of saltus step pin 153 of pressure saltus step device 15 becomes contraction state, and main liquid storage cabin 10 and main pressure chamber 11 break away from; landing pack 122 in the control cabinet 12 freely is scattered and opens, and can land stably by protection assembly and 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.Moreover, on main rocket body, set up the booster-missile combination body, after described booster-missile combination body can break away from main rocket body in main rocket body rising a period of time of assistance and because of depleted of energy, main rocket body still has energy to continue to utilize liquid propulsive thrust to move upward, thereby increased the lifting height of rocket, expanded the range of application of rocket of the present utility model.
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 (10)
1. twin-stage assisted rocket means, it is characterized in that, comprise the booster-missile combination body that main rocket body and at least one and described main rocket body are connected separably, described main rocket body comprises main liquid storage cabin, main pressure chamber, control cabinet and the pressure saltus step device that moves according to the pressure in the described main pressure chamber, described control cabinet is positioned at the top of described main pressure chamber, and described control cabinet is connected by described pressure saltus step device separably with described main pressure chamber, described main liquid storage freight space is communicated with in the bottom of described main pressure chamber and with described main liquid storage cabin, and the bottom in described main liquid storage cabin is provided with the main jet loophole.
2. twin-stage assisted rocket means as claimed in claim 1, it is characterized in that be fixed with the collar on the described main rocket body, the axial line of the described collar is parallel with the axis of described main rocket body, be fixed with connector on the described booster-missile combination body, described connector is sheathed in the described collar.
3. twin-stage assisted rocket means as claimed in claim 2, it is characterized in that, described connector comprises fixed part and the Plug Division that upwards is bent to form along fixed part, described fixed part and described booster-missile combination body are fixed, and described Plug Division can be sheathed in the described collar of described main rocket body up or down.
4. twin-stage assisted rocket means as claimed in claim 2, it is characterized in that, described booster-missile combination body comprises secondary liquid storage cabin and the secondary pressure chamber that is communicated with described secondary liquid storage cabin, described secondary liquid storage bilge portion is provided with the two-stage injection mouth, and described connector is fixed on the described secondary pressure chamber.
5. twin-stage assisted rocket means as claimed in claim 4 is characterized in that, is provided with the secondary breather pipe between described secondary liquid storage cabin and the described secondary pressure chamber, and described secondary liquid storage cabin, described secondary breather pipe and described secondary pressure chamber are communicated with.
6. as each described twin-stage assisted rocket means of claim 1-5, it is characterized in that, the top of the described main pressure chamber of described main rocket body 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 of described pressure chamber and with described ventilation interface and is communicated with, the described relatively ventilation interface of described saltus step air chamber telescopically elasticity is connected in the described pod of described cross groove, 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 of described control cabinet separably.
7. twin-stage assisted rocket means as claimed in claim 6, 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.
8. as each described twin-stage assisted rocket means of claim 1-5, it is characterized in that, described main rocket body also comprises at least two balance wing, described balance wing along described main rocket body circumferentially be installed on the described main liquid storage cabin equably, on the described main pressure chamber or the junction of described main liquid storage cabin and described main pressure chamber.
9. as each described twin-stage assisted rocket means of claim 1-5, it is characterized in that, be provided with main breather pipe between described main liquid storage cabin and the described main pressure chamber, described main liquid storage cabin, described main breather pipe and described main pressure chamber are communicated with.
10. as each described twin-stage assisted rocket means of claim 1-5, it is characterized in that, described main 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220689425 CN203083453U (en) | 2012-12-12 | 2012-12-12 | Two-stage boosting type rocket device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220689425 CN203083453U (en) | 2012-12-12 | 2012-12-12 | Two-stage boosting type rocket device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203083453U true CN203083453U (en) | 2013-07-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220689425 Withdrawn - After Issue CN203083453U (en) | 2012-12-12 | 2012-12-12 | Two-stage boosting type rocket device |
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| CN (1) | CN203083453U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047911A (en) * | 2012-12-12 | 2013-04-17 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN105947229A (en) * | 2016-04-29 | 2016-09-21 | 杨文清 | Air kinetic energy ejection launcher for spacecraft |
-
2012
- 2012-12-12 CN CN 201220689425 patent/CN203083453U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047911A (en) * | 2012-12-12 | 2013-04-17 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN103047911B (en) * | 2012-12-12 | 2014-10-29 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN105947229A (en) * | 2016-04-29 | 2016-09-21 | 杨文清 | Air kinetic energy ejection launcher for spacecraft |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130724 Effective date of abandoning: 20141029 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20130724 Effective date of abandoning: 20141029 |
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| RGAV | Abandon patent right to avoid regrant |