CN111377057A - Self-triggering hydraulic rocket - Google Patents
Self-triggering hydraulic rocket Download PDFInfo
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- CN111377057A CN111377057A CN201811639200.6A CN201811639200A CN111377057A CN 111377057 A CN111377057 A CN 111377057A CN 201811639200 A CN201811639200 A CN 201811639200A CN 111377057 A CN111377057 A CN 111377057A
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- 230000005611 electricity Effects 0.000 claims abstract description 4
- 229910052751 metal Inorganic materials 0.000 claims description 19
- 239000002184 metal Substances 0.000 claims description 19
- 230000005484 gravity Effects 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 3
- 239000010439 graphite Substances 0.000 claims description 3
- 230000001970 hydrokinetic effect Effects 0.000 claims 8
- 229910052802 copper Inorganic materials 0.000 claims 1
- 239000010949 copper Substances 0.000 claims 1
- 230000001960 triggered effect Effects 0.000 abstract description 5
- 229920000742 Cotton Polymers 0.000 description 7
- 241000251468 Actinopterygii Species 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/70—Deployment by springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
- G09B25/02—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes of industrial processes; of machinery
- G09B25/025—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes of industrial processes; of machinery hydraulic; pneumatic
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- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Physics & Mathematics (AREA)
- Educational Administration (AREA)
- Educational Technology (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mechanical Engineering (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention discloses a self-triggering hydrodynamic rocket, which comprises a rocket, a triggering device and an parachute opening device, wherein the rocket comprises: the cabin cover is hinged to the top end of the cabin body and fixed through a cord; the trigger device includes: supporting seat, weight and electrically conductive electric wire, the lower surface of supporting seat is equipped with a conductive tube admittedly, and conductive tube's axle center is perpendicular with the supporting seat, and its drop is sufficient for the original point, and is articulated on the top of original point position and a conducting rod, and the weight is equipped with admittedly in the bottom of conducting rod, and conductive electric wire's one end is connected with conductive tube electricity, and the other end is connected with the conducting rod, is connected with a power and hot flame on conductive electric wire, and the device of opening the umbrella includes: the device comprises an elastic device, a support and an umbrella bag, wherein the support is fixedly arranged at the bottom end of the hatch cover, and the umbrella bag is arranged between the support and the hatch cover. The rocket does not need to rely on a timer or a height setter for presetting time or height, and the ignition device is automatically triggered to ignite when the rocket reaches the highest point, so that the hatch cover is opened, and the flexibility of rocket launching is greatly enhanced.
Description
Technical Field
The invention belongs to the technical field of aviation models, and particularly relates to a self-triggering hydrodynamic rocket.
Background
Hydrodynamic rocket match is a professional match item which is extremely popular in the current aviation model match and has extremely strict requirements on various links of innovative design, manual manufacturing, assembly and debugging and the like of a competitor. How to automatically separate the rocket and make the parachute smoothly pop up and open from the rocket body is a problem which always troubles the players. In a multi-national aircraft design challenge competition (CADC), hydrodynamic rocket projects have great errors on the competition field, so that the main reasons for the failure of the competition and the crash of the rocket are the triggering of separation and the completion of parachute opening.
In the prior art, a trigger device is generally timed by a mechanical timer, a height setter is used for setting the height, and time and height are preset. The estimation result has larger errors due to problems of air resistance, launching angle, launching power and the like, so that the maximum point is not triggered or is triggered in advance.
The parachute is usually installed inside a stretched elastic net and ejected by the elastic force of the elastic. The disadvantages of this open mode are: the rocket body is separated into two parts, two parachutes are needed, and the design of the two parachutes increases the difficulty of parachute opening and reduces the reliability of parachute opening; the umbrella rope is very easy to be wound on the rubber band, so that the umbrella rope cannot be smoothly popped out; the cavity of the ejection net surface formed by the rubber band is extremely large, and the umbrella bag is easy to leak through the rubber band net and cannot be ejected.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a self-triggering hydroelectric rocket, when the parachute of the self-triggering hydroelectric rocket is opened, the cabin bodies are not separated, only one parachute is needed, and the triggering device is more reliable.
Therefore, the technical scheme of the invention is as follows:
a self-triggering hydrodynamic rocket comprising: rocket, trigger device and parachute opening device, the rocket includes: the cabin cover is arranged on the cabin body and is hinged with the cabin body through a hinge part, and the cabin cover is locked with the cabin body through a rope;
the triggering device comprises: the supporting seat is fixedly arranged inside the rocket, the lower surface of the supporting seat is fixedly provided with a cylindrical conductive cylinder with an opening at the lower end, the axis of the conductive cylinder is vertical to the supporting seat, and the vertical foot is the origin, the original point position of the lower surface of the supporting seat is connected with the top end of a conductive rod, the bottom end of the conductive rod is fixedly provided with the heavy hammer capable of conducting electricity, the bottom end of the conductive rod freely moves under the pulling of the gravity of the heavy hammer, one end of the conductive wire is electrically connected with the conductive cylinder, the other end of the conductive wire is electrically connected with the conductive rod, the conductive wire is connected with a power supply and an ignition head close to the wire rope, the heavy hammer can be contacted with the conductive cylinder after the conductive rod is inclined, the conductive cylinder, the conductive wire and the conductive rod form a closed loop, and the ignition head burns and blows the wire rope;
the umbrella opening device comprises: the support is fixedly arranged at the bottom end of the cabin cover, the top surface of the support and one side surface far away from the hinged portion are both open, the umbrella bag is arranged between the support and the cabin cover, one end of the elastic device is fixedly arranged at the top end of the cabin cover, the other end of the elastic device is fixedly arranged on the outer side wall of the cabin body on the same side with the hinged portion, the elastic device is tensioned, and after the rope is disconnected, the cabin cover is opened from the top end of the cabin body by taking the hinged portion as an axis and the umbrella bag is thrown out of the support.
In the above technical solution, the weight and the conductive tube are made of materials that attract each other.
In the above technical solution, the length of the conductive rod is L, the radius of the conductive cylinder is R, the height of the conductive cylinder is H, the weight is a sphere with radius R,
(L+r)2＝R2+H2。
in the above technical solution, the hatch cover and the cabin body are respectively provided with a small hole on one side away from the hinge portion, and the cord passes through the small holes for locking the hatch cover and the cabin body.
In the above technical solution, the bracket includes: the top end of the vertical plate is fixedly mounted with the hatch cover, one side of the bottom plate is fixedly mounted with the bottom end of the vertical plate, and the other side of the bottom plate is far away from the hinged part.
In the above technical scheme, the top end of the conductive rod is connected with the support seat through a first metal ring and a second metal ring, wherein the first metal ring penetrates through the top end of the conductive rod, the second metal ring is connected with the support seat, and the first metal ring and the second metal ring are buckled with each other.
In the above technical scheme, the conductive rod is a graphite rod or a copper wire.
In the above technical scheme, the elastic device is an elastic thread, a supporting part is fixedly installed on the outer side wall of the cabin body which is located below the hinge part and close to the hinge part, the supporting part is used for separating the elastic thread close to the hinge part from the rocket, and the supporting part is a pulley or a block body of which the outer side is formed with an arc surface.
In the above technical solution, the elastic device is a spring.
In the above technical scheme, the hatch cover is a hollow cavity with a closed bottom end.
The beneficial technical effects of the invention are as follows:
1. the triggering device does not need to rely on a timer or a height setter for presetting time or height, when the rocket reaches the highest point, the heavy hammer automatically swings to one side of the cabin body by means of gravity to be in contact with the conductive cylinder to form a triggering circuit of the ignition head, the ignition head is triggered to burn, and the rope is burnt off, so that the cabin cover is opened, the triggering device can be automatically separated according to the actual situation of each launching, and the flexibility of launching the rocket is greatly enhanced;
2. the cabin cover of the rocket is hinged with the cabin body, separation does not occur, the cabin cover laterally pops open after the trigger device is triggered, and the cabin cover and the cabin body complete landing through a parachute, so that the problems of winding and overlapping impact of the two parts caused by the fact that the rocket is separated into the two parts and two parachutes are needed are solved;
3. the device places the parachute package on the support by means of the principle that the stone thrower throws the object, and throws out the parachute package by means of the inertia of the ejection of the hatch cover while the hatch cover laterally pops open, so that the problem that the parachute package is in contact with the elastic net to cause winding is avoided, and the reliability of parachute opening is greatly enhanced.
Drawings
Fig. 1 is a schematic view of an embodiment 1 of a self-triggering hydrodynamic rocket according to the present invention (with the hatch open in dashed lines);
fig. 2 is a schematic view of a triggering device of embodiment 1 of the self-triggering hydrodynamic rocket according to the present invention (the dotted line is the triggering state);
fig. 3 is a schematic view of embodiment 4 of the self-triggering hydrodynamic rocket of the present invention.
Wherein, 1: ignition head, 2: power supply, 3: supporting seat, 4: support portion, 5: conductive barrel, 6: conductive rod, 7: weight, 8: hatch, 9: umbrella bag, 10: a bracket, 11: elastic means, 12: a cabin body.
Detailed Description
In order to make the technical solution of the present invention better understood, the technical solution of the present invention is further described below with reference to specific examples.
Example 1
As shown in fig. 1 to 3, the device comprises: rocket, trigger device and parachute opening device, the rocket includes: the cabin cover 8 is covered on the cabin body 12 and is hinged with the cabin body 12 through a hinge part which can be a hinge; the hatch 8 is locked with the cabin 12 by a cord.
The trigger device includes: the supporting seat 3, the weight 7 and the conductive wire, the supporting seat 3 is fixedly arranged inside the rocket and can be arranged in the cabin cover 8 or the cabin body 12. The supporting seat 3 is preferably made of an insulating material, metal subjected to insulating treatment can be used to prevent the short circuit of the trigger device, and the influence on the overall launching performance of the rocket caused by the change of the overall weight of the trigger device is considered when the material is selected. The lower surface of the supporting seat 3 is fixedly provided with a cylindrical conductive cylinder 5 with an open lower end, the axis of the conductive cylinder 5 is perpendicular to the supporting seat 3 and is vertical to the supporting seat 3, the origin point position of the lower surface of the supporting seat 3 is connected with the top end of a conductive rod 6, the bottom end of the conductive rod 6 is fixedly provided with a heavy hammer 7 capable of conducting electricity, the bottom end of the conductive rod 6 freely moves under the pulling of the gravity of the heavy hammer 7, one end of a conductive wire is electrically connected with the conductive cylinder 5, the other end of the conductive wire is electrically connected with the conductive rod 6, the conductive wire is connected with a power supply 2 (lithium battery) and an ignition head 1 close to a cord, so that when the cabin body 12 inclines, the conductive rod 6 also inclines, the heavy hammer 7 can be in contact with the conductive cylinder 5, the conductive wire and the conductive rod 6 form a closed loop.
The umbrella opening device includes: the device comprises an elastic device 11, a support 10 and an umbrella bag 9, wherein the support 10 is fixedly arranged at the bottom end of a cabin cover 8, the top surface of the support 10 and one side surface far away from a hinge part are both open, the umbrella bag 9 is arranged between the support 10 and the cabin cover 8, one end of the elastic device 11 is fixedly arranged at the top end of the cabin cover 8, the other end of the elastic device 11 is fixedly arranged on the outer side wall of a cabin body 12 on the same side with the hinge part, and the distance between two fixed ends of the elastic device 11 is as far as possible so as to ensure.
The elastic means 11 are tensioned and when the cord is broken, the hatch 8 is opened from the top of the cabin 12 about the hinge and the umbrella bag 9 is ejected from the support 10.
The power supply 2 can be installed at any position inside the cabin 12 for fixing as long as the burning cord of the ignition head 1 is not affected.
Example 2
In example 1, the weight 7 and the conductive tube 5 are attracted to each other by, for example: the weight is a conductive soft magnet, and the conductive tube 5 is a conductive permanent magnet. After the conductive rod 6 is inclined, the weight 7 can contact with the conductive tube 5 and is pulled by magnetic force to continuously contact. At this time, the included angle between the conductive rod 6 and the axis of the conductive tube 5 is a trigger angle.
The length of the conductive rod 6 is L, the radius of the conductive tube 5 is R (neglecting the wall thickness of the conductive tube 5), the height of the conductive tube 5 is H, the weight 7 is a sphere with radius R,
the trigger angle is 45-60 degrees, and accidental triggering is prevented. Or according to transmitted vibrationsSize, launch angle, and other factors fine-tune the angle to prevent accidental triggering are primary considerations. In addition, in order to make the weight 7 contact the conductive tube 5 better, (L + r)2＝R2+H2。
When the conducting rod 6 is in contact with the conducting cylinder 5, the total resistance of a circuit formed by the conducting cylinder 5, the ignition head 1, the power supply 2, the conducting wire and the conducting rod 6 in a closed state is less than 8 omega, so that the ignition head can be ensured to be ignited smoothly.
One sides of the hatch cover 8 and the cabin body 12 far away from the hinged part are respectively provided with small holes, and a rope passes through the 2 small holes and is used for locking the hatch cover 8 and the cabin body 12. The cotton rope can comprise 2 cotton threads and a fish tape, wherein, connect a cotton thread on the aperture of cabin cover 8 and cabin body 12 respectively, two cotton threads link together through a fish tape again, its aim at, the cotton thread is soft but be difficult to burn out fast, the fish tape material is hard inconvenient operation but the contact fire source breaks off immediately, so earlier with 2 cotton threads respectively with cabin cover 8 fixed with cabin body 12, pass through a fish tape fixed connection with 2 cotton threads again, the operation of being more convenient for like this. The ignition head 1 is fixed on the fishing line by using an adhesive tape, and the ignition head 1 is positioned outside the rocket. The fishing line and the ignition head can also penetrate through a thin paper tube at the same time, and the ignition head is clamped and fixed in the thin paper tube. The fixing method of the ignition head is not limited to this, and any fixing method may be used as long as it is favorable for the ignition head to blow the fishing line.
Example 3
In order to smoothly eject the umbrella bag, on the basis of embodiment 2, the support 10 includes: the cabin cover 8 is a hollow cavity with a closed bottom end, the top end of the vertical plate is fixedly mounted with the cabin cover 8, one side of the bottom plate is fixedly mounted with the bottom end of the vertical plate, and the other side of the bottom plate is far away from the hinged part. The bottom end surfaces of the bracket 10 and the hatch cover 8 are both made of wood and are polished smoothly so as to reduce the friction force when the umbrella bag 9 is thrown out. The particular configuration of the stand 10 is not limited thereto and it is sufficient to ensure that the bag can be contained and ejected whilst minimising the friction of the bag as it is ejected.
In order to ensure that the heavy hammer of the trigger device can rotate flexibly, a double-ring type connection mode is adopted: the top end of the conductive rod 6 is connected with the supporting seat 3 through a first metal ring and a second metal ring, wherein the first metal ring penetrates through the top end of the conductive rod 6, the second metal ring is connected with the supporting seat 3, and the first metal ring and the second metal ring are buckled with each other.
The conductive rod 6 is a graphite rod or a copper wire.
In order to ensure that the conducting rod of the trigger device is coaxial with the cabin body 12 in the rocket vertical state and improve the running reliability of the trigger device, the supporting seat 3 is fixedly arranged in the cavity body of the cabin cover 8. When the support base 3 is a circular plate, the support base 3 is coaxially and fixedly installed inside the hatch cover 8.
Example 4
On the basis of embodiment 3, the elastic device 11 is an elastic thread, a supporting portion 4 is fixedly installed on the outer side wall of the cabin 12 which is located below the hinge portion and close to the hinge portion, the supporting portion 4 is used for separating the elastic thread close to the hinge portion from the rocket, and the supporting portion 4 is a pulley or a block body of which the outer side is formed with an arc surface. The cabin 12 has a diameter D0In order to ensure that the hatch cover 8 is opened smoothly after the cord is disconnected, the length of the supporting part 4 in the direction parallel to the diameter of the cabin body 12 is larger than D0/2。
Example 5
In addition to embodiment 3, the elastic means 11 is a spring.
The working principle of the self-triggering hydrodynamic rocket comprises the following steps:
under the vertical state of the self-triggering hydrodynamic rocket, the heavy hammer naturally droops and points to the ground. Hydrodynamic rocket rises to the air and moves along the parabola, when hydrodynamic rocket rises to the peak, power consumption is almost exhausted, the gravity center is greatly deviated to the top end (top weight) of the rocket, the law causes the rocket to turn around the direction when the peak speed is zero, the heavy hammer is deviated to one side of the cabin, the conducting rod is in contact with the conducting tube, meanwhile, the trigger circuit (the circuit formed by the conducting tube, the ignition head, the power supply and the conducting rod) is communicated, and the ignition head ignites and burns. After the ignition head burns, the cord is heated and fused, the hatch cover pops open under the elastic force action of the elastic device, the umbrella bag is thrown out by means of the inertia of the hatch cover popping open, and the umbrella bag is opened after being subjected to air resistance, so that the umbrella opening action is completed.
The invention gets rid of the unreliability brought by triggering the umbrella opening through the preset height or time in the prior art, and the umbrella bag and the elastic device are respectively arranged inside and outside the cabin body, thereby thoroughly avoiding the condition that the umbrella fails to open due to the winding of the pull rope of the umbrella bag and the elastic device. The self-triggering hydrodynamic rocket is simple in structure, reliable in implementation, low in manufacturing cost and suitable for application in the technical field of aeromodels.
Spatially relative terms, such as "upper," "lower," "left," "right," and the like, may be used in the embodiments for ease of description to describe one element or feature's relationship to another element or feature as illustrated in the figures. It will be understood that the spatial terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary term "lower" can encompass both an upper and a lower orientation. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
Moreover, relational terms such as "first" and "second," and the like, may be used solely to distinguish one element from another element having the same name, without necessarily requiring or implying any actual such relationship or order between such elements.
The invention has been described in an illustrative manner, and it is to be understood that any simple variations, modifications or other equivalent changes which can be made by one skilled in the art without departing from the spirit of the invention fall within the scope of the invention.
Claims (10)
1. A self-triggering hydrodynamic rocket, comprising: rocket, trigger device and parachute opening device, the rocket includes: the device comprises a cabin cover (8) and a cabin body (12) with an open top end, wherein the cabin cover (8) covers the cabin body (12) and is hinged with the cabin body (12) through a hinge part, and the cabin cover (8) is locked with the cabin body (12) through a rope;
the triggering device comprises: the rocket comprises a supporting seat (3), a heavy hammer (7) and a conductive wire, wherein the supporting seat (3) is fixedly arranged inside the rocket, a cylindrical conductive cylinder (5) with an opening at the lower end is fixedly arranged on the lower surface of the supporting seat (3), the axis of the conductive cylinder (5) is vertical to the supporting seat (3) and is a vertical foot as an origin, the origin position of the lower surface of the supporting seat (3) is connected with the top end of a conductive rod (6), the bottom end of the conductive rod (6) is fixedly provided with the heavy hammer (7) capable of conducting electricity, the bottom end of the conductive rod (6) freely moves under the pulling of the gravity of the heavy hammer (7), one end of the conductive wire is electrically connected with the conductive cylinder (5), the other end of the conductive wire is electrically connected with the conductive rod (6), a power supply (2) and an ignition head (1) close to the heavy hammer are connected to the conductive wire, and the conductive rod (6) can be in contact with the conductive cylinder (5) after being inclined, the conductive cylinder (5), the conductive wire and the conductive rod (6) form a closed loop, and the ignition head (1) burns and blows the wire rope;
the umbrella opening device comprises: the umbrella bag comprises an elastic device (11), a support (10) and an umbrella bag (9), wherein the support (10) is fixedly arranged at the bottom end of the cabin cover (8), the top surface of the support (10) and one side surface far away from the hinged portion are both open, the umbrella bag (9) is arranged between the support (10) and the cabin cover (8), one end of the elastic device (11) is fixedly arranged at the top end of the cabin cover (8), the other end of the elastic device is fixedly arranged on the outer side wall of the cabin body (12) on the same side with the hinged portion, the elastic device (11) is tensioned, and after a rope is disconnected, the cabin cover (8) is opened from the top end of the cabin body (12) by taking the hinged portion as an axis and the umbrella bag (9) is thrown out of the support (10).
2. Self-triggering hydrokinetic rocket according to claim 1, wherein the weight (7) and the conductive tube (5) are mutually attracted.
3. Self-triggering hydrodynamic rocket according to claim 1 or 2, characterized in that the length of the conductive rod (6) is L, the radius of the conductive barrel (5) is R, the height of the conductive barrel (5) is H, the weight (7) is a sphere with radius R,
(L+r)2＝R2+H2。
4. self-triggering hydrokinetic rocket according to claim 3, wherein the hatch (8) and the tank (12) are provided with respective small holes on the sides remote from the hinge, said cords passing through 2 of said small holes for locking the hatch (8) and the tank (12).
5. Self-triggering hydrokinetic rocket according to claim 4, wherein the carriage (10) comprises: the top end of the vertical plate is fixedly mounted with the hatch cover (8), one side of the bottom plate is fixedly mounted with the bottom end of the vertical plate, and the other side of the bottom plate is far away from the hinged portion.
6. Self-triggering hydrokinetic rocket according to claim 5, wherein the top end of the electrically conductive rod (6) is connected to the support base (3) by a first metal ring and a second metal ring, wherein the first metal ring passes through the top end of the electrically conductive rod (6), the second metal ring is connected to the support base (3), and the first metal ring and the second metal ring are fastened to each other.
7. Self-triggering hydrokinetic rocket according to claim 6, wherein the electrically conductive rods (6) are graphite rods or copper wires.
8. Self-triggering hydrokinetic rocket according to claim 7, wherein the elastic means (11) is an elastic thread, a support part (4) is fixedly mounted on the outer side wall of the hull (12) below and close to the hinge part for separating the elastic thread close to the hinge part from the rocket, the support part (4) is a pulley or a block with an outer side formed with an arc surface.
9. Self-triggering hydrokinetic rocket according to claim 7, wherein said elastic means (11) are springs.
10. Self-triggering hydrokinetic rocket according to claim 8 or 9, wherein the hatch (8) is a hollow body closed at the bottom end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811639200.6A CN111377057A (en) | 2018-12-29 | 2018-12-29 | Self-triggering hydraulic rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811639200.6A CN111377057A (en) | 2018-12-29 | 2018-12-29 | Self-triggering hydraulic rocket |
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| CN111377057A true CN111377057A (en) | 2020-07-07 |
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| CN201811639200.6A Pending CN111377057A (en) | 2018-12-29 | 2018-12-29 | Self-triggering hydraulic rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247270A (en) * | 2021-06-16 | 2021-08-13 | 中国人民解放军国防科技大学 | Water rocket parachute bay device |
| CN113324446A (en) * | 2021-06-16 | 2021-08-31 | 中国人民解放军国防科技大学 | Fixing and separating device for water rocket boosting glider |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113247270A (en) * | 2021-06-16 | 2021-08-13 | 中国人民解放军国防科技大学 | Water rocket parachute bay device |
| CN113324446A (en) * | 2021-06-16 | 2021-08-31 | 中国人民解放军国防科技大学 | Fixing and separating device for water rocket boosting glider |
| CN113324446B (en) * | 2021-06-16 | 2023-01-31 | 中国人民解放军国防科技大学 | Fixing and separating device for water rocket boosting glider |
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